Initial revision
This commit is contained in:
j4strngs
commit
82b9d18f24
1769 changed files with 58660 additions and 0 deletions
16
AUTHORS
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16
AUTHORS
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@ -0,0 +1,16 @@
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Authors of the Flight Gear project.
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Flight Gear is a group project and has many contributors. I have
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attempted to make a complete list of people in the ``Thanks'' file
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||||
located in the top level directory of this file.
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My name is Curt Olson <curt@me.umn.edu>. I am the primary organizer
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of this project. I maintain the official source code and run the FG
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web site.
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My intention is to mention all the contributors to the FG project in
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the ``Thanks file''. Unfortunately, being human, I have likely missed
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a few people. If you have made a contribution, and don't find
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yourself listed in the ``Thanks'' file, ***PLEASE*** drop me a quick
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reminder. No contribution is too small to be overlooked!!!
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||||
65
Aircraft-uiuc/Beech99/aircraft.dat
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65
Aircraft-uiuc/Beech99/aircraft.dat
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@ -0,0 +1,65 @@
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# Jeff Scott
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# Beech 99, low cruise configuration
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# small twin turboprop commuter airplane, data from:
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# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
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# Controls, Part I. Lawrence KS: DARcorporation, 1995,
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# pg 508-510
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# 03-23-2000 file creation
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init Dz_cg 2.5 # [ft]
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geometry bw 46 # [ft]
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geometry cbar 6.5 # [ft]
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geometry Sw 280 # [ft^2]
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controlSurface de 20 20 # [deg] guess for now
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controlSurface da 20 20 # [deg] guess for now
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controlSurface dr 20 20 # [deg] guess for now
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||||
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||||
mass Weight 7000 # [lb]
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mass I_xx 10085 # [slug-ft^2]
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mass I_yy 15148 # [slug-ft^2]
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mass I_zz 23046 # [slug-ft^2]
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mass I_xz 1600 # [slug-ft^2]
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# Roskam: CTx=0.162 (SL conditions) --> 1550 lb
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# aircraft specs: two engines of 553 kW each
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# ~2300 lb static thrust each
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engine simpleSingle 2300 # [lb]
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CL CLo 0.201 # []
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CL CL_a 5.48 # [/rad]
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CL CL_adot 2.5 # [/rad]
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CL CL_q 8.1 # [/rad]
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CL CL_de 0.6 # [/rad]
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CD CDo 0.027 # []
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#CD CDK # []
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CD CD_a 0.131 # [/rad]
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CD CD_de 0.0 # [/rad]
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Cm Cmo 0.05 # []
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Cm Cm_a -1.89 # [/rad]
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Cm Cm_adot -9.1 # [/rad]
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Cm Cm_q -34.0 # [/rad]
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Cm Cm_de -2.0 # [/rad]
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CY CY_beta -0.59 # [/rad]
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CY CY_p -0.19 # [/rad]
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CY CY_r 0.39 # [/rad]
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CY CY_da 0.0 # [/rad] sign reversed
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CY CY_dr 0.148 # [/rad]
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Cl Cl_beta -0.13 # [/rad]
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Cl Cl_p -0.5 # [/rad]
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Cl Cl_r 0.14 # [/rad]
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Cl Cl_da -0.156 # [/rad] sign reversed
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Cl Cl_dr 0.0109 # [/rad]
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Cn Cn_beta 0.08 # [/rad]
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Cn Cn_p 0.0109 # [/rad]
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Cn Cn_r -0.197 # [/rad]
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Cn Cn_da 0.0012 # [/rad] sign reversed
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Cn Cn_dr -0.0772 # [/rad]
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64
Aircraft-uiuc/Boeing747/aircraft.dat
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64
Aircraft-uiuc/Boeing747/aircraft.dat
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@ -0,0 +1,64 @@
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# Jeff Scott
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# Boeing 747, low cruise configuration
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# large commercial jetliner, data from:
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# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
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# Controls, Part I. Lawrence KS: DARcorporation, 1995,
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# pg 543-545
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# 03-23-2000 file creation
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init Dz_cg 0.0 # [ft]
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geometry bw 196.0 # [ft]
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geometry cbar 27.3 # [ft]
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geometry Sw 5500.0 # [ft^2]
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controlSurface de 20 20 # [deg] guess for now
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controlSurface da 20 20 # [deg] guess for now
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controlSurface dr 20 20 # [deg] guess for now
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mass Weight 636640 # [lb]
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mass I_xx 18200000 # [slug-ft^2]
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mass I_yy 33100000 # [slug-ft^2]
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mass I_zz 49700000 # [slug-ft^2]
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mass I_xz 970000 # [slug-ft^2]
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|
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# Roskam: CTx=0.025 (SL conditions) --> 39500 lb
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# aircraft specs: 4 engines of 41000 lb static thrust each (747-100)
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# 63500 lb static thrust each (747-400)
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engine simpleSingle 39500 # [lb]
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CL CLo 0.210 # []
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CL CL_a 4.40 # [/rad]
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CL CL_adot 7.0 # [/rad]
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CL CL_q 6.6 # [/rad]
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CL CL_de 0.32 # [/rad]
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CD CDo 0.0164 # []
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CD CD_a 0.200 # [/rad]
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CD CD_de 0.0 # [/rad]
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Cm Cmo 0.0 # []
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Cm Cm_a -1.0 # [/rad]
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Cm Cm_adot -4.0 # [/rad]
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Cm Cm_q -20.5 # [/rad]
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Cm Cm_de -1.3 # [/rad]
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CY CY_beta -0.9 # [/rad]
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CY CY_p 0.0 # [/rad]
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CY CY_r 0.0 # [/rad]
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CY CY_da 0.0 # [/rad] sign reversed
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CY CY_dr 0.120 # [/rad]
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Cl Cl_beta -0.160 # [/rad]
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Cl Cl_p -0.340 # [/rad]
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Cl Cl_r 0.130 # [/rad]
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Cl Cl_da -0.013 # [/rad] sign reversed
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Cl Cl_dr 0.008 # [/rad]
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Cn Cn_beta 0.16 # [/rad]
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Cn Cn_p -0.026 # [/rad]
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Cn Cn_r -0.280 # [/rad]
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Cn Cn_da -0.0018 # [/rad] sign reversed
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Cn Cn_dr -0.1 # [/rad]
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13
Aircraft-uiuc/Cessna172-71/CLfa.dat
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13
Aircraft-uiuc/Cessna172-71/CLfa.dat
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@ -0,0 +1,13 @@
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# C172 CL as function of alpha
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-4.984732818 -0.14
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0 0.31
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10.02676141 1.21
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11.97481792 1.376
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13.75098708 1.51249
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15.01149423 1.591
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||||
15.9282267 1.63
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||||
17.36062119 1.60878
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17.99087477 1.53712
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19.0221988 1.376
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21.02755108 1.142
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61
Aircraft-uiuc/Cessna172-71/aircraft.dat
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61
Aircraft-uiuc/Cessna172-71/aircraft.dat
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@ -0,0 +1,61 @@
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# Jeff Scott
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# Cessna 172
|
||||
# small single piston engine general aviation airplane
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# This model was adapted from the file c172_aero.c in Flight
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# Gear developed by Tony Peden. This version uses stability
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# derivatives and a CL-alpha curve. The aircraft data comes from:
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# Tony Peden's c172_aero.c and c172_init.c files
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# 02-01-2000 file creation
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init Dz_cg 2.5 # [ft] FG c172_aero.c
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init nondim_rate_V_rel_wind
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geometry bw 35.8 # [ft] FG c172_aero.c
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geometry cbar 4.90 # [ft] FG c172_aero.c
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geometry Sw 174.0 # [ft^2] FG c172_aero.c
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controlSurface de 28 23 # [deg] FG c172_aero.c
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controlSurface da 20 15 # [deg] FG c172_aero.c
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controlSurface dr 16 16 # [deg] FG c172_aero.c
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mass Weight 2300.0 # [lb] FG c172_init.c
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mass I_xx 948.0 # [slug-ft^2] FG c172_init.c
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mass I_yy 1346.0 # [slug-ft^2] FG c172_init.c
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mass I_zz 1967.0 # [slug-ft^2] FG c172_init.c
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mass I_xz 0.0 # [slug-ft^2] FG c172_init.c
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engine c172
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CL CL_adot 1.7 # [/rad] FG c172_aero.c
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CL CL_q 3.9 # [/rad] FG c172_aero.c
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CL CL_de 0.43 # [/rad] FG c172_aero.c
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CL CLfa Aircraft-uiuc/Cessna172-71/CLfa.dat 0 1 # [] FG c172_aero.c
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CD CDo 0.031 # [] FG c172_aero.c
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CD CDK 0.054 # [] FG c172_aero.c
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#CD CD_a 0.13 # [/rad] FG c172_aero.c
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CD CD_de 0.06 # [/rad] FG c172_aero.c
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Cm Cmo -0.015 # [] FG c172_aero.c
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Cm Cm_a -0.89 # [/rad] FG c172_aero.c
|
||||
Cm Cm_adot -5.2 # [/rad] FG c172_aero.c
|
||||
Cm Cm_q -12.4 # [/rad] FG c172_aero.c
|
||||
Cm Cm_de -1.28 # [/rad] FG c172_aero.c
|
||||
|
||||
CY CY_beta -0.31 # [/rad] FG c172_aero.c
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||||
CY CY_p -0.037 # [/rad] FG c172_aero.c
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||||
CY CY_r 0.21 # [/rad] FG c172_aero.c
|
||||
CY CY_da 0.0 # [/rad] FG c172_aero.c
|
||||
CY CY_dr 0.187 # [/rad] FG c172_aero.c
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||||
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||||
Cl Cl_beta -0.089 # [/rad] FG c172_aero.c
|
||||
Cl Cl_p -0.47 # [/rad] FG c172_aero.c
|
||||
Cl Cl_r 0.096 # [/rad] FG c172_aero.c
|
||||
Cl Cl_da -0.178 # [/rad] FG c172_aero.c
|
||||
Cl Cl_dr 0.0147 # [/rad] FG c172_aero.c
|
||||
|
||||
Cn Cn_beta 0.065 # [/rad] FG c172_aero.c
|
||||
Cn Cn_p -0.03 # [/rad] FG c172_aero.c
|
||||
Cn Cn_r -0.099 # [/rad] FG c172_aero.c
|
||||
Cn Cn_da -0.053 # [/rad] FG c172_aero.c
|
||||
Cn Cn_dr -0.0657 # [/rad] FG c172_aero.c
|
||||
11
Aircraft-uiuc/Cessna172-73/CLfa.dat
Normal file
11
Aircraft-uiuc/Cessna172-73/CLfa.dat
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|
@ -0,0 +1,11 @@
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# C172 CL as function of alpha
|
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|
||||
-4.984732818 -0.22
|
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0 0.25
|
||||
8.021409132 1.02
|
||||
12.0321137 1.252
|
||||
13.75098708 1.354
|
||||
14.89690267 1.44
|
||||
16.04281826 1.466
|
||||
17.76169165 1.298
|
||||
20.05352283 0.97
|
||||
61
Aircraft-uiuc/Cessna172-73/aircraft.dat
Normal file
61
Aircraft-uiuc/Cessna172-73/aircraft.dat
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|
@ -0,0 +1,61 @@
|
|||
# Jeff Scott
|
||||
# Cessna 172
|
||||
# small single piston engine general aviation airplane
|
||||
# This model was adapted from the file c172_aero.c in Flight
|
||||
# Gear developed by Tony Peden. This version uses stability
|
||||
# derivatives and a CL-alpha curve. The aircraft data comes from:
|
||||
# Tony Peden's c172_aero.c and c172_init.c files (FG 0.7.3)
|
||||
# 05-04-2000 file creation
|
||||
|
||||
init Dz_cg 2.5 # [ft] FG c172_aero.c
|
||||
init nondim_rate_V_rel_wind
|
||||
|
||||
geometry bw 35.8 # [ft] FG c172_aero.c
|
||||
geometry cbar 4.90 # [ft] FG c172_aero.c
|
||||
geometry Sw 174.0 # [ft^2] FG c172_aero.c
|
||||
|
||||
controlSurface de 28 23 # [deg] FG c172_aero.c
|
||||
controlSurface da 20 15 # [deg] FG c172_aero.c
|
||||
controlSurface dr 16 16 # [deg] FG c172_aero.c
|
||||
|
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mass Weight 2300.0 # [lb] FG c172_init.c
|
||||
mass I_xx 948.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_yy 1346.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_zz 1967.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_xz 0.0 # [slug-ft^2] FG c172_init.c
|
||||
|
||||
engine c172
|
||||
|
||||
CL CL_adot 1.7 # [/rad] FG c172_aero.c
|
||||
CL CL_q 3.9 # [/rad] FG c172_aero.c
|
||||
CL CL_de 0.34763715 # [/rad] FG c172_aero.c
|
||||
CL CLfa Aircraft-uiuc/Cessna172-73/CLfa.dat 0 1 # [] FG c172_aero.c
|
||||
|
||||
CD CDo 0.036 # [] FG c172_aero.c
|
||||
CD CDK 0.0830304 # [] FG c172_aero.c
|
||||
#CD CD_a 0.13 # [/rad] FG c172_aero.c
|
||||
CD CD_de 0.06 # [/rad] FG c172_aero.c
|
||||
|
||||
Cm Cmo -0.020 # [] FG c172_aero.c
|
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Cm Cm_a -1.80 # [/rad] FG c172_aero.c
|
||||
Cm Cm_adot -5.2 # [/rad] FG c172_aero.c
|
||||
Cm Cm_q -12.4 # [/rad] FG c172_aero.c
|
||||
Cm Cm_de -1.28 # [/rad] FG c172_aero.c
|
||||
|
||||
CY CY_beta -0.31 # [/rad] FG c172_aero.c
|
||||
CY CY_p -0.037 # [/rad] FG c172_aero.c
|
||||
CY CY_r 0.21 # [/rad] FG c172_aero.c
|
||||
CY CY_da 0.0 # [/rad] FG c172_aero.c
|
||||
CY CY_dr 0.187 # [/rad] FG c172_aero.c
|
||||
|
||||
Cl Cl_beta -0.089 # [/rad] FG c172_aero.c
|
||||
Cl Cl_p -0.47 # [/rad] FG c172_aero.c
|
||||
Cl Cl_r 0.096 # [/rad] FG c172_aero.c
|
||||
Cl Cl_da -0.090 # [/rad] FG c172_aero.c
|
||||
Cl Cl_dr 0.0147 # [/rad] FG c172_aero.c
|
||||
|
||||
Cn Cn_beta 0.065 # [/rad] FG c172_aero.c
|
||||
Cn Cn_p -0.03 # [/rad] FG c172_aero.c
|
||||
Cn Cn_r -0.099 # [/rad] FG c172_aero.c
|
||||
Cn Cn_da -0.0053 # [/rad] FG c172_aero.c
|
||||
Cn Cn_dr -0.0657 # [/rad] FG c172_aero.c
|
||||
146
Aircraft-uiuc/Cessna172/aircraft.dat
Normal file
146
Aircraft-uiuc/Cessna172/aircraft.dat
Normal file
|
|
@ -0,0 +1,146 @@
|
|||
# Jeff Scott
|
||||
# Cessna 172
|
||||
# small single piston engine general aviation airplane
|
||||
# This model was adapted from the file c172_aero.c in Flight
|
||||
# Gear developed by Tony Peden. This version uses stability
|
||||
# derivatives only. The aircraft data comes from:
|
||||
# Tony Peden's c172_aero.c and c172_init.c files
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 480-482. (actually Cessna 182)
|
||||
# 02-01-2000 file creation
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
init nondim_rate_V_rel_wind
|
||||
|
||||
geometry bw 35.8 # [ft] FG c172_aero.c
|
||||
geometry cbar 4.90 # [ft] FG c172_aero.c
|
||||
geometry Sw 174.0 # [ft^2] FG c172_aero.c
|
||||
|
||||
controlSurface de 28 23 # [deg] FG c172_aero.c
|
||||
controlSurface da 20 15 # [deg] FG c172_aero.c
|
||||
controlSurface dr 16 16 # [deg] FG c172_aero.c
|
||||
|
||||
mass Weight 2300.0 # [lb] FG c172_init.c
|
||||
mass I_xx 948.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_yy 1346.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_zz 1967.0 # [slug-ft^2] FG c172_init.c
|
||||
mass I_xz 0.0 # [slug-ft^2] FG c172_init.c
|
||||
|
||||
engine c172
|
||||
|
||||
CL CLo 0.31 # [] FG c172_aero.c (from CL-a curve)
|
||||
CL CL_a 5.143 # [/rad] FG c172_aero.c (from CL-a curve)
|
||||
CL CL_adot 1.7 # [/rad] FG c172_aero.c
|
||||
CL CL_q 3.9 # [/rad] FG c172_aero.c
|
||||
CL CL_de 0.43 # [/rad] FG c172_aero.c
|
||||
#CL CLfa CLfa.dat 0 1 # [] FG c172_aero.c
|
||||
|
||||
CD CDo 0.031 # [] FG c172_aero.c
|
||||
CD CDK 0.054 # [] FG c172_aero.c
|
||||
#CD CD_a 0.13 # [/rad] FG c172_aero.c
|
||||
CD CD_de 0.06 # [/rad] FG c172_aero.c
|
||||
|
||||
Cm Cmo -0.015 # [] FG c172_aero.c
|
||||
Cm Cm_a -0.89 # [/rad] FG c172_aero.c
|
||||
Cm Cm_adot -5.2 # [/rad] FG c172_aero.c
|
||||
Cm Cm_q -12.4 # [/rad] FG c172_aero.c
|
||||
Cm Cm_de -1.28 # [/rad] FG c172_aero.c
|
||||
|
||||
CY CY_beta -0.31 # [/rad] FG c172_aero.c
|
||||
CY CY_p -0.037 # [/rad] FG c172_aero.c
|
||||
CY CY_r 0.21 # [/rad] FG c172_aero.c
|
||||
CY CY_da 0.0 # [/rad] FG c172_aero.c
|
||||
CY CY_dr 0.187 # [/rad] FG c172_aero.c
|
||||
|
||||
Cl Cl_beta -0.089 # [/rad] FG c172_aero.c
|
||||
Cl Cl_p -0.47 # [/rad] FG c172_aero.c
|
||||
Cl Cl_r 0.096 # [/rad] FG c172_aero.c
|
||||
Cl Cl_da -0.178 # [/rad] FG c172_aero.c
|
||||
Cl Cl_dr 0.0147 # [/rad] FG c172_aero.c
|
||||
|
||||
Cn Cn_beta 0.065 # [/rad] FG c172_aero.c
|
||||
Cn Cn_p -0.03 # [/rad] FG c172_aero.c
|
||||
Cn Cn_r -0.099 # [/rad] FG c172_aero.c
|
||||
Cn Cn_da -0.053 # [/rad] FG c172_aero.c
|
||||
Cn Cn_dr -0.0657 # [/rad] FG c172_aero.c
|
||||
|
||||
*
|
||||
|
||||
# * above denotes end of data to read in.
|
||||
# uncommenting this line will produced the uiuc_record.dat
|
||||
# file (flight data recorder file)
|
||||
|
||||
#record Dx_pilot # [ft] x-location
|
||||
#record Dy_pilot # [ft] y-loaction
|
||||
#record Dz_pilot # [ft] z-location
|
||||
record V_north # [ft/s] x-velocity
|
||||
record V_east # [ft/s] y-velocity
|
||||
record V_down # [ft/s] z-velocity
|
||||
record V_rel_wind # [ft/s] total velocity
|
||||
record Dynamic_pressure # [lb/ft^2] dynamic pressure
|
||||
record Alpha # [rad] angle of attack
|
||||
record Alpha_dot # [rad/s] rate of change of alpha
|
||||
record Beta # [rad] sideslip angle
|
||||
record Beta_dot # [rad/s] rate of change of beta
|
||||
#record Gamma # [rad] flight path angle
|
||||
#record P_body # [rad] roll rate
|
||||
#record Q_body # [rad] pitch rate
|
||||
#record R_body # [rad] yaw rate
|
||||
#record Phi # [rad] bank angle
|
||||
#record Theta # [rad] pitch attitude angle
|
||||
#record Theta_dot # [rad] rate change of theta
|
||||
#record Psi # [rad] heading angle
|
||||
#record long_trim
|
||||
#record trim_inc
|
||||
#record Density # [slug/ft^3] air density
|
||||
#record Mass # [slug] aircraft mass
|
||||
#record Simtime # [s] current sim time
|
||||
#record dt # [s] current time step
|
||||
record elevator # [rad] elevator deflection
|
||||
record aileron # [rad] aileron deflection
|
||||
record rudder # [rad] rudder deflection
|
||||
#record CDfaI # [] CD(alpha)
|
||||
#record CDfadeI # [] CD(alpha,delta_e)
|
||||
#record CD # [] drag coefficient
|
||||
#record CLfaI # [] CL(alpha)
|
||||
#record CLfadeI # [] CL(alpha,delta_e)
|
||||
record CL # [] lift coefficient
|
||||
#record CmfadeI # [] Cm(alpha,delta_e)
|
||||
#record Cm # [] pitch moment coefficient
|
||||
#record CYfadaI # [] CY(alpha,delta_a)
|
||||
#record CYfadrI # [] CY(alpha,delta_r)
|
||||
#record CY # [] side-force coefficient
|
||||
#record ClfadaI # [] Cl(alpha,delta_a)
|
||||
#record ClfadrI # [] Cl(alpha,delta_r)
|
||||
#record Cl # [] roll moment coefficient
|
||||
#record CnfadaI # [] Cn(alpha,delta_a)
|
||||
#record CnfadrI # [] Cn(alpha,delta_r)
|
||||
#record Cn # [] yaw moment coefficient
|
||||
#record F_X_wind # [lb] aero x-force in wind-axes
|
||||
#record F_Y_wind # [lb] aero y-force in wind-axes
|
||||
#record F_Z_wind # [lb] aero z-force in wind-axes
|
||||
#record F_X_aero # [lb] aero x-force in body-axes
|
||||
#record F_Y_aero # [lb] aero y-force in body-axes
|
||||
#record F_Z_aero # [lb] aero z-force in body-axes
|
||||
#record F_X_engine # [lb] prop x-force in body-axes
|
||||
#record F_Y_engine # [lb] prop y-force in body-axes
|
||||
#record F_Z_engine # [lb] prop z-force in body-axes
|
||||
#record F_X_gear # [lb] gear x-force in body-axes
|
||||
#record F_Y_gear # [lb] gear y-force in body-axes
|
||||
#record F_Z_gear # [lb] gear z-force in body-axes
|
||||
#record F_X # [lb] total x-force in body-axes
|
||||
#record F_Y # [lb] total y-force in body-axes
|
||||
#record F_Z # [lb] total z-force in body-axes
|
||||
#record M_l_aero # [ft-lb] aero roll moment in body axes
|
||||
#record M_m_aero # [ft-lb] aero pitch moment in body axes
|
||||
#record M_n_aero # [ft-lb] aero yaw moment in body axes
|
||||
#record M_l_engine # [ft-lb] prop roll moment in body axes
|
||||
#record M_m_engine # [ft-lb] prop pitch moment in body axes
|
||||
#record M_n_engine # [ft-lb] prop yaw moment in body axes
|
||||
#record M_l_gear # [ft-lb] gear roll moment in body axes
|
||||
#record M_m_gear # [ft-lb] gear pitch moment in body axes
|
||||
#record M_n_gear # [ft-lb] gear yaw moment in body axes
|
||||
#record M_l_rp # [ft-lb] total roll moment in body axes
|
||||
#record M_m_rp # [ft-lb] total pitch moment in body axes
|
||||
#record M_n_rp # [ft-lb] total yaw moment in body axes
|
||||
64
Aircraft-uiuc/Cessna310/aircraft.dat
Normal file
64
Aircraft-uiuc/Cessna310/aircraft.dat
Normal file
|
|
@ -0,0 +1,64 @@
|
|||
# Jeff Scott
|
||||
# Cessna 310, cruise configuration
|
||||
# small twin piston engine general aviation airplane, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 487-489
|
||||
# 03-23-2000 file creation
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
|
||||
geometry bw 36.9 # [ft]
|
||||
geometry cbar 4.79 # [ft]
|
||||
geometry Sw 175.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 4600 # [lb]
|
||||
mass I_xx 8884 # [slug-ft^2]
|
||||
mass I_yy 1939 # [slug-ft^2]
|
||||
mass I_zz 11001 # [slug-ft^2]
|
||||
mass I_xz 0 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.031 (cruise conditions) --> 500 lb
|
||||
# aircraft specs: 2 engines of 213 kW each
|
||||
# ~1100 lb static thrust each
|
||||
engine simpleSingle 1100 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.288 # []
|
||||
CL CL_a 4.58 # [/rad]
|
||||
CL CL_adot 5.3 # [/rad]
|
||||
CL CL_q 9.7 # [/rad]
|
||||
CL CL_de 0.81 # [/rad]
|
||||
|
||||
CD CDo 0.029 # []
|
||||
CD CD_a 0.16 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.07 # []
|
||||
Cm Cm_a -0.137 # [/rad]
|
||||
Cm Cm_adot -12.7 # [/rad]
|
||||
Cm Cm_q -26.3 # [/rad]
|
||||
Cm Cm_de -2.26 # [/rad]
|
||||
|
||||
CY CY_beta -0.698 # [/rad]
|
||||
CY CY_p -0.141 # [/rad]
|
||||
CY CY_r 0.355 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.23 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.1096 # [/rad]
|
||||
Cl Cl_p -0.551 # [/rad]
|
||||
Cl Cl_r 0.0729 # [/rad]
|
||||
Cl Cl_da -0.172 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.0192 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.1444 # [/rad]
|
||||
Cn Cn_p -0.0257 # [/rad]
|
||||
Cn Cn_r -0.1495 # [/rad]
|
||||
Cn Cn_da 0.0168 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.1152 # [/rad]
|
||||
63
Aircraft-uiuc/Cessna620/aircraft.dat
Normal file
63
Aircraft-uiuc/Cessna620/aircraft.dat
Normal file
|
|
@ -0,0 +1,63 @@
|
|||
# Jeff Scott
|
||||
# Cessna 620, cruise configuration
|
||||
# four piston engine business airplane, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 515-517
|
||||
# 03-23-2000 file creation
|
||||
|
||||
init Dz_cg 4.0 # [ft]
|
||||
|
||||
geometry bw 55.1 # [ft]
|
||||
geometry cbar 6.58 # [ft]
|
||||
geometry Sw 340 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 15000 # [lb]
|
||||
mass I_xx 64811 # [slug-ft^2]
|
||||
mass I_yy 17300 # [slug-ft^2]
|
||||
mass I_zz 64543 # [slug-ft^2]
|
||||
mass I_xz 0 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.042 (cruise conditions) --> 1300 lb
|
||||
# aurcraft specs: 4 engines, power unknown
|
||||
engine simpleSingle 2500 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.48 # []
|
||||
CL CL_a 5.55 # [/rad]
|
||||
CL CL_adot 2.7 # [/rad]
|
||||
CL CL_q 7.5 # [/rad]
|
||||
CL CL_de 0.58 # [/rad]
|
||||
|
||||
CD CDo 0.0322 # []
|
||||
CD CD_a 0.269 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.06 # []
|
||||
Cm Cm_a -1.18 # [/rad]
|
||||
Cm Cm_adot -8.17 # [/rad]
|
||||
Cm Cm_q -22.4 # [/rad]
|
||||
Cm Cm_de -1.73 # [/rad]
|
||||
|
||||
CY CY_beta -0.883 # [/rad]
|
||||
CY CY_p -0.227 # [/rad]
|
||||
CY CY_r 0.448 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.2 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.1381 # [/rad]
|
||||
Cl Cl_p -0.566 # [/rad]
|
||||
Cl Cl_r 0.1166 # [/rad]
|
||||
Cl Cl_da -0.1776 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.02 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.1739 # [/rad]
|
||||
Cn Cn_p -0.0501 # [/rad]
|
||||
Cn Cn_r -0.2 # [/rad]
|
||||
Cn Cn_da 0.0194 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.1054 # [/rad]
|
||||
59
Aircraft-uiuc/Convair880/aircraft.dat
Normal file
59
Aircraft-uiuc/Convair880/aircraft.dat
Normal file
|
|
@ -0,0 +1,59 @@
|
|||
# Michael Selig
|
||||
# Convair 880, cruise configuration (M .8 @ 35kft)
|
||||
# medium commercial jetliner, data from:
|
||||
# Robert Nelson, "Flight Stability and Automatic Control", 2nd ed.
|
||||
# p 414-415
|
||||
# 02-10-2000 file creation
|
||||
|
||||
init Dz_cg 0.0 # [ft]
|
||||
|
||||
geometry bw 120. # [ft]
|
||||
geometry cbar 18.94 # [ft]
|
||||
geometry Sw 2000.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 126000 # [lb]
|
||||
mass I_xx 115000 # [slug-ft^2]
|
||||
mass I_yy 2450000 # [slug-ft^2]
|
||||
mass I_zz 4070000 # [slug-ft^2]
|
||||
mass I_xz 0 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 4 engines of 15000 lb static thrust each
|
||||
engine simpleSingle 30000 # [lb] guess
|
||||
|
||||
|
||||
CL CLo 0.347 # []
|
||||
CL CL_a 4.8 # [/rad]
|
||||
CL CL_adot 2.7 # [/rad]
|
||||
CL CL_q 7.5 # [/rad]
|
||||
CL CL_de 0.19 # [/rad]
|
||||
|
||||
CD CDo 0.024 # []
|
||||
CD CD_a 0.150 # [/rad]
|
||||
|
||||
Cm Cmo 0.0 # []
|
||||
Cm Cm_a -0.650 # [/rad]
|
||||
Cm Cm_adot -4.5 # [/rad]
|
||||
Cm Cm_q -4.5 # [/rad]
|
||||
Cm Cm_de -0.570 # [/rad]
|
||||
|
||||
CY CY_beta -0.812 # [/rad]
|
||||
CY CY_p 0.0 # [/rad]
|
||||
CY CY_r 0.184 # [/rad]
|
||||
CY CY_dr 0.019 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.117 # [/rad]
|
||||
Cl Cl_p -0.312 # [/rad]
|
||||
Cl Cl_r 0.153 # [/rad]
|
||||
Cl Cl_da -0.050 # [/rad]
|
||||
Cl Cl_dr 0.019 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.129 # [/rad]
|
||||
Cn Cn_p -0.011 # [/rad]
|
||||
Cn Cn_r -0.165 # [/rad]
|
||||
Cn Cn_da 0.008 # [/rad]
|
||||
Cn Cn_dr -0.076 # [/rad]
|
||||
65
Aircraft-uiuc/F104/aircraft.dat
Normal file
65
Aircraft-uiuc/F104/aircraft.dat
Normal file
|
|
@ -0,0 +1,65 @@
|
|||
# Jeff Scott
|
||||
# Lockheed F-104, cruise configuration
|
||||
# small single jet engine supersonic fighter, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 529-531
|
||||
# 03-23-2000 file creation
|
||||
|
||||
init Dz_cg 3.0 # [ft]
|
||||
|
||||
geometry bw 21.9 # [ft]
|
||||
geometry cbar 9.6 # [ft]
|
||||
geometry Sw 196.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 16300 # [lb]
|
||||
mass I_xx 3600 # [slug-ft^2]
|
||||
mass I_yy 59000 # [slug-ft^2]
|
||||
mass I_zz 60000 # [slug-ft^2]
|
||||
mass I_xz 0 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.2634 (SL conditions) --> 5050 lb
|
||||
# aircraft specs: 7800 lb static thrust (F-104A)
|
||||
# 15800 lb static thrust (F-104G)
|
||||
# 18800 lb static thrust (F-104S)
|
||||
engine simpleSingle 8000 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.122 # []
|
||||
CL CL_a 2.005 # [/rad]
|
||||
CL CL_adot 0.82 # [/rad]
|
||||
CL CL_q 1.9 # [/rad]
|
||||
CL CL_de 0.684 # [/rad] used CLih (typo in Roskam?)
|
||||
|
||||
CD CDo 0.048 # []
|
||||
CD CD_a 0.384 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo -0.028 # []
|
||||
Cm Cm_a -1.308 # [/rad]
|
||||
Cm Cm_adot -2.05 # [/rad]
|
||||
Cm Cm_q -4.83 # [/rad]
|
||||
Cm Cm_de -1.6 # [/rad] used Cmih (typo in Roskam?)
|
||||
|
||||
CY CY_beta -1.045 # [/rad]
|
||||
CY CY_p 0.0 # [/rad]
|
||||
CY CY_r 0.0 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.087 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.093 # [/rad]
|
||||
Cl Cl_p -0.272 # [/rad]
|
||||
Cl Cl_r 0.154 # [/rad]
|
||||
Cl Cl_da -0.0173 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.0079 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.242 # [/rad]
|
||||
Cn Cn_p -0.093 # [/rad]
|
||||
Cn Cn_r -0.649 # [/rad]
|
||||
Cn Cn_da -0.0025 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.0435 # [/rad]
|
||||
64
Aircraft-uiuc/F4/aircraft.dat
Normal file
64
Aircraft-uiuc/F4/aircraft.dat
Normal file
|
|
@ -0,0 +1,64 @@
|
|||
# Michael Selig
|
||||
# F-4 Phantom, subsonic cruise configuration
|
||||
# twin jet engine supersonic fighter/attack airplane, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 536-538
|
||||
# 02-10-2000 file creation
|
||||
|
||||
init Dz_cg 5.0 # [ft]
|
||||
|
||||
geometry bw 38.7 # [ft]
|
||||
geometry cbar 16.0 # [ft]
|
||||
geometry Sw 530.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 39000 # [lb]
|
||||
mass I_xx 25000 # [slug-ft^2]
|
||||
mass I_yy 122200 # [slug-ft^2]
|
||||
mass I_zz 139800 # [slug-ft^2]
|
||||
mass I_xz 2200 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.2 (SL conditions) --> 6670 lb
|
||||
# aircraft specs: 2 engines of 16000 lb static thrust each (F-4A)
|
||||
# 2 engines of 17900 lb static thrust each (F-4E)
|
||||
engine simpleSingle 16000 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.100 # []
|
||||
CL CL_a 3.750 # [/rad]
|
||||
CL CL_adot 0.86 # [/rad]
|
||||
CL CL_q 1.8 # [/rad]
|
||||
CL CL_de 0.40 # [/rad] used CLih (typo in Roskam?)
|
||||
|
||||
CD CDo 0.0205 # []
|
||||
CD CD_a 0.300 # [/rad]
|
||||
CD CD_de -0.10 # [/rad] used CDih (typo in Roskam?)
|
||||
|
||||
Cm Cmo 0.025 # []
|
||||
Cm Cm_a -0.400 # [/rad]
|
||||
Cm Cm_adot -1.3 # [/rad]
|
||||
Cm Cm_q -2.7 # [/rad]
|
||||
Cm Cm_de -0.580 # [/rad] used Cmih (typo in Roskam?)
|
||||
|
||||
CY CY_beta -0.68 # [/rad]
|
||||
CY CY_p 0.0 # [/rad]
|
||||
CY CY_r 0.0 # [/rad]
|
||||
CY CY_da 0.016 # [/rad] sign reversed
|
||||
CY CY_dr 0.095 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.080 # [/rad]
|
||||
Cl Cl_p -0.240 # [/rad]
|
||||
Cl Cl_r 0.070 # [/rad]
|
||||
Cl Cl_da -0.042 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.0060 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.125 # [/rad]
|
||||
Cn Cn_p -0.036 # [/rad]
|
||||
Cn Cn_r -0.270 # [/rad]
|
||||
Cn Cn_da 0.0010 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.066 # [/rad]
|
||||
63
Aircraft-uiuc/Learjet24/aircraft.dat
Normal file
63
Aircraft-uiuc/Learjet24/aircraft.dat
Normal file
|
|
@ -0,0 +1,63 @@
|
|||
# Michael Selig
|
||||
# Learjet 24, max weight cruise configuration
|
||||
# twin jet-engine business jet, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 522-524
|
||||
# 02-10-2000 file creation
|
||||
|
||||
init Dz_cg 3.5 # [ft]
|
||||
|
||||
geometry bw 34. # [ft]
|
||||
geometry cbar 7.0 # [ft]
|
||||
geometry Sw 230.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 13000 # [lb]
|
||||
mass I_xx 28000 # [slug-ft^2]
|
||||
mass I_yy 18800 # [slug-ft^2]
|
||||
mass I_zz 47000 # [slug-ft^2]
|
||||
mass I_xz 1300 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.256 (SL conditions) --> 2020 lb
|
||||
# aircraft specs: 2 engines of 2950 lb static thrust each
|
||||
engine simpleSingle 2950 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.130 # []
|
||||
CL CL_a 5.840 # [/rad]
|
||||
CL CL_adot 2.2 # [/rad]
|
||||
CL CL_q 4.7 # [/rad]
|
||||
CL CL_de 0.46 # [/rad]
|
||||
|
||||
CD CDo 0.0216 # []
|
||||
CD CD_a 0.300 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.05 # []
|
||||
Cm Cm_a -0.64 # [/rad]
|
||||
Cm Cm_adot -6.7 # [/rad]
|
||||
Cm Cm_q -15.5 # [/rad]
|
||||
Cm Cm_de -1.24 # [/rad]
|
||||
|
||||
CY CY_beta -0.730 # [/rad]
|
||||
CY CY_p 0.0 # [/rad]
|
||||
CY CY_r 0.400 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.140 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.110 # [/rad]
|
||||
Cl Cl_p -0.450 # [/rad]
|
||||
Cl Cl_r 0.160 # [/rad]
|
||||
Cl Cl_da -0.178 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.019 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.127 # [/rad]
|
||||
Cn Cn_p -0.008 # [/rad]
|
||||
Cn Cn_r -0.200 # [/rad]
|
||||
Cn Cn_da 0.020 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.074 # [/rad]
|
||||
64
Aircraft-uiuc/Marchetti/aircraft.dat
Normal file
64
Aircraft-uiuc/Marchetti/aircraft.dat
Normal file
|
|
@ -0,0 +1,64 @@
|
|||
# Michael Selig
|
||||
# SIAI-Marchetti S-211, cruise configuration (1)
|
||||
# small, single jet engine, military trainer, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 494-496
|
||||
# 02-10-2000 file creation
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
|
||||
geometry bw 26.3 # [ft]
|
||||
geometry cbar 5.4 # [ft]
|
||||
geometry Sw 136.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 4000 # [lb]
|
||||
mass I_xx 800 # [slug-ft^2]
|
||||
mass I_yy 4800 # [slug-ft^2]
|
||||
mass I_zz 5200 # [slug-ft^2]
|
||||
mass I_xz 200 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.022 (cruise conditions) --> 600 lb
|
||||
# aircraft specs: 2500 lb static thrust
|
||||
#engine simpleSingle 1250 # [lb]
|
||||
engine simpleSingle 3500 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.149 # []
|
||||
CL CL_a 5.50 # [/rad]
|
||||
CL CL_adot 4.2 # [/rad]
|
||||
CL CL_q 10.0 # [/rad]
|
||||
CL CL_de 0.38 # [/rad]
|
||||
|
||||
CD CDo 0.0205 # []
|
||||
CD CD_a 0.12 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo -0.08 # []
|
||||
Cm Cm_a -0.24 # [/rad]
|
||||
Cm Cm_adot -9.6 # [/rad]
|
||||
Cm Cm_q -17.7 # [/rad]
|
||||
Cm Cm_de -0.88 # [/rad]
|
||||
|
||||
CY CY_beta -1.00 # [/rad]
|
||||
CY CY_p -0.140 # [/rad]
|
||||
CY CY_r 0.61 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.0280 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.110 # [/rad]
|
||||
Cl Cl_p -0.390 # [/rad]
|
||||
Cl Cl_r 0.280 # [/rad]
|
||||
Cl Cl_da -0.100 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.050 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.170 # [/rad]
|
||||
Cn Cn_p 0.090 # [/rad]
|
||||
Cn Cn_r -0.260 # [/rad]
|
||||
Cn Cn_da 0.003 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.120 # [/rad]
|
||||
28
Aircraft-uiuc/Pioneer-TD/CDfa.dat
Normal file
28
Aircraft-uiuc/Pioneer-TD/CDfa.dat
Normal file
|
|
@ -0,0 +1,28 @@
|
|||
# Pioneer CD as function of alpha [deg]
|
||||
|
||||
-8 0.0734
|
||||
-7 0.0674
|
||||
-6 0.0629
|
||||
-5 0.0597
|
||||
-4 0.0576
|
||||
-3 0.0568
|
||||
-2 0.0569
|
||||
-1 0.0580
|
||||
0 0.0601
|
||||
1 0.0630
|
||||
2 0.0668
|
||||
3 0.0713
|
||||
4 0.0767
|
||||
5 0.0830
|
||||
6 0.0900
|
||||
7 0.0980
|
||||
8 0.1069
|
||||
9 0.1167
|
||||
10 0.1276
|
||||
11 0.1397
|
||||
12 0.1530
|
||||
13 0.1676
|
||||
14 0.1837
|
||||
15 0.2014
|
||||
16 0.2209
|
||||
17 0.2423
|
||||
244
Aircraft-uiuc/Pioneer-TD/CDfade.dat
Normal file
244
Aircraft-uiuc/Pioneer-TD/CDfade.dat
Normal file
|
|
@ -0,0 +1,244 @@
|
|||
# Pioneer change in CD as function of alpha and elevator defection
|
||||
|
||||
-20
|
||||
-7 0.0231
|
||||
-6 0.0209
|
||||
-5 0.0187
|
||||
-4 0.0166
|
||||
-3 0.0147
|
||||
-2 0.0129
|
||||
-1 0.0113
|
||||
0 0.0098
|
||||
1 0.0086
|
||||
2 0.0074
|
||||
3 0.0063
|
||||
4 0.0053
|
||||
5 0.0043
|
||||
6 0.0031
|
||||
7 0.0017
|
||||
8 0.0001
|
||||
9 -0.002
|
||||
10 -0.0046
|
||||
11 -0.0079
|
||||
12 -0.012
|
||||
13 -0.0171
|
||||
14 -0.0234
|
||||
15 -0.0311
|
||||
16 -0.0403
|
||||
17 -0.0543
|
||||
|
||||
-15
|
||||
-7 0.0178
|
||||
-6 0.0155
|
||||
-5 0.0135
|
||||
-4 0.0117
|
||||
-3 0.0101
|
||||
-2 0.0086
|
||||
-1 0.0073
|
||||
0 0.0061
|
||||
1 0.005
|
||||
2 0.004
|
||||
3 0.003
|
||||
4 0.002
|
||||
5 0.001
|
||||
6 0
|
||||
7 -0.001
|
||||
8 -0.002
|
||||
9 -0.0031
|
||||
10 -0.0042
|
||||
11 -0.0054
|
||||
12 -0.0067
|
||||
13 -0.008
|
||||
14 -0.0094
|
||||
15 -0.0109
|
||||
16 -0.0125
|
||||
17 -0.0141
|
||||
|
||||
-10
|
||||
-7 0.0111
|
||||
-6 0.0095
|
||||
-5 0.0081
|
||||
-4 0.0069
|
||||
-3 0.0057
|
||||
-2 0.0047
|
||||
-1 0.0038
|
||||
0 0.003
|
||||
1 0.0022
|
||||
2 0.0015
|
||||
3 0.0008
|
||||
4 0.0001
|
||||
5 -0.0006
|
||||
6 -0.0013
|
||||
7 -0.002
|
||||
8 -0.0027
|
||||
9 -0.0035
|
||||
10 -0.0042
|
||||
11 -0.005
|
||||
12 -0.0058
|
||||
13 -0.0067
|
||||
14 -0.0075
|
||||
15 -0.0084
|
||||
16 -0.0093
|
||||
17 -0.0102
|
||||
|
||||
-5
|
||||
-7 0.0058
|
||||
-6 0.005
|
||||
-5 0.0043
|
||||
-4 0.0037
|
||||
-3 0.0031
|
||||
-2 0.0025
|
||||
-1 0.002
|
||||
0 0.0016
|
||||
1 0.0011
|
||||
2 0.0007
|
||||
3 0.0003
|
||||
4 -0.0001
|
||||
5 -0.0005
|
||||
6 -0.0009
|
||||
7 -0.0013
|
||||
8 -0.0018
|
||||
9 -0.0022
|
||||
10 -0.0027
|
||||
11 -0.0032
|
||||
12 -0.0037
|
||||
13 -0.0043
|
||||
14 -0.0048
|
||||
15 -0.0054
|
||||
16 -0.006
|
||||
17 -0.0066
|
||||
|
||||
0
|
||||
-7 0
|
||||
-6 0
|
||||
-5 0
|
||||
-4 0
|
||||
-3 0
|
||||
-2 0
|
||||
-1 0
|
||||
0 0
|
||||
1 0
|
||||
2 0
|
||||
3 0
|
||||
4 0
|
||||
5 0
|
||||
6 0
|
||||
7 0
|
||||
8 0
|
||||
9 0
|
||||
10 0
|
||||
11 0
|
||||
12 0
|
||||
13 0
|
||||
14 0
|
||||
15 0
|
||||
16 0
|
||||
17 0
|
||||
|
||||
5
|
||||
-7 -0.0028
|
||||
-6 -0.0021
|
||||
-5 -0.0015
|
||||
-4 -0.001
|
||||
-3 -0.0006
|
||||
-2 -0.0003
|
||||
-1 0
|
||||
0 0.0003
|
||||
1 0.0005
|
||||
2 0.0007
|
||||
3 0.001
|
||||
4 0.0012
|
||||
5 0.0014
|
||||
6 0.0016
|
||||
7 0.0018
|
||||
8 0.002
|
||||
9 0.0023
|
||||
10 0.0025
|
||||
11 0.0028
|
||||
12 0.0031
|
||||
13 0.0035
|
||||
14 0.0038
|
||||
15 0.0041
|
||||
16 0.0045
|
||||
17 0.0048
|
||||
|
||||
10
|
||||
-7 -0.0053
|
||||
-6 -0.0037
|
||||
-5 -0.0024
|
||||
-4 -0.0014
|
||||
-3 -0.0005
|
||||
-2 0.0002
|
||||
-1 0.0008
|
||||
0 0.0013
|
||||
1 0.0018
|
||||
2 0.0022
|
||||
3 0.0026
|
||||
4 0.003
|
||||
5 0.0034
|
||||
6 0.0039
|
||||
7 0.0044
|
||||
8 0.005
|
||||
9 0.0056
|
||||
10 0.0063
|
||||
11 0.007
|
||||
12 0.0078
|
||||
13 0.0086
|
||||
14 0.0095
|
||||
15 0.0103
|
||||
16 0.0111
|
||||
17 0.0119
|
||||
|
||||
15
|
||||
-7 -0.0063
|
||||
-6 -0.0043
|
||||
-5 -0.0025
|
||||
-4 -0.001
|
||||
-3 0.0002
|
||||
-2 0.0013
|
||||
-1 0.0022
|
||||
0 0.0031
|
||||
1 0.0039
|
||||
2 0.0046
|
||||
3 0.0053
|
||||
4 0.006
|
||||
5 0.0068
|
||||
6 0.0076
|
||||
7 0.0084
|
||||
8 0.0093
|
||||
9 0.0102
|
||||
10 0.0112
|
||||
11 0.0122
|
||||
12 0.0133
|
||||
13 0.0144
|
||||
14 0.0155
|
||||
15 0.0167
|
||||
16 0.0177
|
||||
17 0.0188
|
||||
|
||||
20
|
||||
-7 -0.0029
|
||||
-6 -0.0007
|
||||
-5 0.0012
|
||||
-4 0.0028
|
||||
-3 0.0042
|
||||
-2 0.0053
|
||||
-1 0.0064
|
||||
0 0.0074
|
||||
1 0.0082
|
||||
2 0.0091
|
||||
3 0.0099
|
||||
4 0.0108
|
||||
5 0.0117
|
||||
6 0.0126
|
||||
7 0.0136
|
||||
8 0.0147
|
||||
9 0.0158
|
||||
10 0.017
|
||||
11 0.0182
|
||||
12 0.0195
|
||||
13 0.0209
|
||||
14 0.0222
|
||||
15 0.0236
|
||||
16 0.025
|
||||
17 0.0263
|
||||
28
Aircraft-uiuc/Pioneer-TD/CLfa.dat
Normal file
28
Aircraft-uiuc/Pioneer-TD/CLfa.dat
Normal file
|
|
@ -0,0 +1,28 @@
|
|||
# Pioneer CL as function of alpha [deg]
|
||||
|
||||
-8 -0.384
|
||||
-7 -0.294
|
||||
-6 -0.202
|
||||
-5 -0.107
|
||||
-4 -0.010
|
||||
-3 0.088
|
||||
-2 0.187
|
||||
-1 0.286
|
||||
0 0.385
|
||||
1 0.483
|
||||
2 0.580
|
||||
3 0.674
|
||||
4 0.766
|
||||
5 0.855
|
||||
6 0.940
|
||||
7 1.022
|
||||
8 1.098
|
||||
9 1.170
|
||||
10 1.235
|
||||
11 1.295
|
||||
12 1.347
|
||||
13 1.392
|
||||
14 1.430
|
||||
15 1.458
|
||||
16 1.478
|
||||
17 1.488
|
||||
244
Aircraft-uiuc/Pioneer-TD/CLfade.dat
Normal file
244
Aircraft-uiuc/Pioneer-TD/CLfade.dat
Normal file
|
|
@ -0,0 +1,244 @@
|
|||
# Pioneer change in CD as function of alpha and elevator defection
|
||||
|
||||
-20
|
||||
-7 -0.088
|
||||
-6 -0.093
|
||||
-5 -0.098
|
||||
-4 -0.103
|
||||
-3 -0.106
|
||||
-2 -0.11
|
||||
-1 -0.113
|
||||
0 -0.116
|
||||
1 -0.118
|
||||
2 -0.119
|
||||
3 -0.121
|
||||
4 -0.122
|
||||
5 -0.122
|
||||
6 -0.123
|
||||
7 -0.123
|
||||
8 -0.122
|
||||
9 -0.122
|
||||
10 -0.121
|
||||
11 -0.119
|
||||
12 -0.118
|
||||
13 -0.116
|
||||
14 -0.114
|
||||
15 -0.112
|
||||
16 -0.109
|
||||
17 -0.107
|
||||
|
||||
-15
|
||||
-7 -0.075
|
||||
-6 -0.079
|
||||
-5 -0.083
|
||||
-4 -0.087
|
||||
-3 -0.091
|
||||
-2 -0.094
|
||||
-1 -0.097
|
||||
0 -0.1
|
||||
1 -0.102
|
||||
2 -0.105
|
||||
3 -0.107
|
||||
4 -0.108
|
||||
5 -0.11
|
||||
6 -0.111
|
||||
7 -0.111
|
||||
8 -0.111
|
||||
9 -0.111
|
||||
10 -0.11
|
||||
11 -0.109
|
||||
12 -0.108
|
||||
13 -0.106
|
||||
14 -0.103
|
||||
15 -0.1
|
||||
16 -0.097
|
||||
17 -0.093
|
||||
|
||||
-10
|
||||
-7 -0.057
|
||||
-6 -0.061
|
||||
-5 -0.064
|
||||
-4 -0.067
|
||||
-3 -0.07
|
||||
-2 -0.072
|
||||
-1 -0.074
|
||||
0 -0.076
|
||||
1 -0.078
|
||||
2 -0.079
|
||||
3 -0.079
|
||||
4 -0.08
|
||||
5 -0.08
|
||||
6 -0.08
|
||||
7 -0.08
|
||||
8 -0.079
|
||||
9 -0.078
|
||||
10 -0.077
|
||||
11 -0.075
|
||||
12 -0.073
|
||||
13 -0.071
|
||||
14 -0.068
|
||||
15 -0.065
|
||||
16 -0.062
|
||||
17 -0.058
|
||||
|
||||
-5
|
||||
-7 -0.036
|
||||
-6 -0.038
|
||||
-5 -0.04
|
||||
-4 -0.041
|
||||
-3 -0.043
|
||||
-2 -0.044
|
||||
-1 -0.045
|
||||
0 -0.045
|
||||
1 -0.045
|
||||
2 -0.045
|
||||
3 -0.045
|
||||
4 -0.045
|
||||
5 -0.044
|
||||
6 -0.043
|
||||
7 -0.042
|
||||
8 -0.041
|
||||
9 -0.04
|
||||
10 -0.038
|
||||
11 -0.037
|
||||
12 -0.035
|
||||
13 -0.033
|
||||
14 -0.031
|
||||
15 -0.029
|
||||
16 -0.027
|
||||
17 -0.025
|
||||
|
||||
0
|
||||
-7 0
|
||||
-6 0
|
||||
-5 0
|
||||
-4 0
|
||||
-3 0
|
||||
-2 0
|
||||
-1 0
|
||||
0 0
|
||||
1 0
|
||||
2 0
|
||||
3 0
|
||||
4 0
|
||||
5 0
|
||||
6 0
|
||||
7 0
|
||||
8 0
|
||||
9 0
|
||||
10 0
|
||||
11 0
|
||||
12 0
|
||||
13 0
|
||||
14 0
|
||||
15 0
|
||||
16 0
|
||||
17 0
|
||||
|
||||
5
|
||||
-7 0.025
|
||||
-6 0.026
|
||||
-5 0.027
|
||||
-4 0.027
|
||||
-3 0.028
|
||||
-2 0.029
|
||||
-1 0.03
|
||||
0 0.03
|
||||
1 0.031
|
||||
2 0.031
|
||||
3 0.032
|
||||
4 0.032
|
||||
5 0.032
|
||||
6 0.032
|
||||
7 0.032
|
||||
8 0.032
|
||||
9 0.032
|
||||
10 0.032
|
||||
11 0.031
|
||||
12 0.03
|
||||
13 0.029
|
||||
14 0.028
|
||||
15 0.027
|
||||
16 0.025
|
||||
17 0.024
|
||||
|
||||
10
|
||||
-7 0.058
|
||||
-6 0.059
|
||||
-5 0.06
|
||||
-4 0.061
|
||||
-3 0.062
|
||||
-2 0.063
|
||||
-1 0.064
|
||||
0 0.065
|
||||
1 0.066
|
||||
2 0.066
|
||||
3 0.067
|
||||
4 0.067
|
||||
5 0.068
|
||||
6 0.068
|
||||
7 0.068
|
||||
8 0.068
|
||||
9 0.067
|
||||
10 0.066
|
||||
11 0.065
|
||||
12 0.064
|
||||
13 0.062
|
||||
14 0.061
|
||||
15 0.058
|
||||
16 0.055
|
||||
17 0.052
|
||||
|
||||
15
|
||||
-7 0.093
|
||||
-6 0.093
|
||||
-5 0.094
|
||||
-4 0.095
|
||||
-3 0.096
|
||||
-2 0.097
|
||||
-1 0.098
|
||||
0 0.099
|
||||
1 0.099
|
||||
2 0.1
|
||||
3 0.1
|
||||
4 0.1
|
||||
5 0.1
|
||||
6 0.1
|
||||
7 0.099
|
||||
8 0.098
|
||||
9 0.096
|
||||
10 0.094
|
||||
11 0.092
|
||||
12 0.089
|
||||
13 0.086
|
||||
14 0.082
|
||||
15 0.078
|
||||
16 0.073
|
||||
17 0.068
|
||||
|
||||
20
|
||||
-7 0.1
|
||||
-6 0.101
|
||||
-5 0.101
|
||||
-4 0.102
|
||||
-3 0.103
|
||||
-2 0.104
|
||||
-1 0.106
|
||||
0 0.107
|
||||
1 0.108
|
||||
2 0.11
|
||||
3 0.111
|
||||
4 0.112
|
||||
5 0.113
|
||||
6 0.113
|
||||
7 0.114
|
||||
8 0.113
|
||||
9 0.113
|
||||
10 0.111
|
||||
11 0.11
|
||||
12 0.107
|
||||
13 0.104
|
||||
14 0.1
|
||||
15 0.096
|
||||
16 0.09
|
||||
17 0.084
|
||||
16
Aircraft-uiuc/Pioneer-TD/CYfbetadr.dat
Normal file
16
Aircraft-uiuc/Pioneer-TD/CYfbetadr.dat
Normal file
|
|
@ -0,0 +1,16 @@
|
|||
# Pioneer change in CY as function of beta and rudder deflection
|
||||
|
||||
-20
|
||||
-20 0.19
|
||||
0 0.24
|
||||
20 0.29
|
||||
|
||||
0
|
||||
-20 -0.05
|
||||
0 0
|
||||
20 0.05
|
||||
|
||||
20
|
||||
-20 -0.25
|
||||
0 -0.22
|
||||
20 -0.18
|
||||
155
Aircraft-uiuc/Pioneer-TD/Clfada.dat
Normal file
155
Aircraft-uiuc/Pioneer-TD/Clfada.dat
Normal file
|
|
@ -0,0 +1,155 @@
|
|||
# Pioneer change in Cl as function of alpha and aileron deflection
|
||||
|
||||
-5
|
||||
-10.31 0.014
|
||||
-8.22 0.0143
|
||||
-6.12 0.0148
|
||||
-4.01 0.0148
|
||||
-1.91 0.0153
|
||||
0.2 0.0158
|
||||
2.29 0.016
|
||||
4.4 0.016
|
||||
6.5 0.0152
|
||||
8.59 0.0144
|
||||
10.65 0.0128
|
||||
12.71 0.0118
|
||||
13.72 0.0109
|
||||
14.73 0.0105
|
||||
15.74 0.0093
|
||||
16.75 0.0093
|
||||
17.75 0.0087
|
||||
18.75 0.0073
|
||||
19.74 0.0061
|
||||
20.73 0.0016
|
||||
|
||||
0
|
||||
-10.31 0
|
||||
-8.22 0
|
||||
-6.12 0
|
||||
-4.01 0
|
||||
-1.91 0
|
||||
0.2 0
|
||||
2.29 0
|
||||
4.4 0
|
||||
6.5 0
|
||||
8.59 0
|
||||
10.65 0
|
||||
12.71 0
|
||||
13.72 0
|
||||
14.73 0
|
||||
15.74 0
|
||||
16.75 0
|
||||
17.75 0
|
||||
18.75 0
|
||||
19.74 0
|
||||
20.73 0
|
||||
|
||||
5
|
||||
-10.31 -0.014
|
||||
-8.22 -0.0143
|
||||
-6.12 -0.0148
|
||||
-4.01 -0.0148
|
||||
-1.91 -0.0153
|
||||
0.2 -0.0158
|
||||
2.29 -0.016
|
||||
4.4 -0.016
|
||||
6.5 -0.0152
|
||||
8.59 -0.0144
|
||||
10.65 -0.0128
|
||||
12.71 -0.0118
|
||||
13.72 -0.0109
|
||||
14.73 -0.0105
|
||||
15.74 -0.0093
|
||||
16.75 -0.0093
|
||||
17.75 -0.0087
|
||||
18.75 -0.0073
|
||||
19.74 -0.0061
|
||||
20.73 -0.0016
|
||||
|
||||
10
|
||||
-10.31 -0.028
|
||||
-8.22 -0.0281
|
||||
-6.12 -0.0292
|
||||
-4.01 -0.0299
|
||||
-1.91 -0.0296
|
||||
0.2 -0.0299
|
||||
2.29 -0.0308
|
||||
4.4 -0.0308
|
||||
6.5 -0.0295
|
||||
8.59 -0.0279
|
||||
10.65 -0.026
|
||||
12.71 -0.0238
|
||||
13.72 -0.0222
|
||||
14.73 -0.0202
|
||||
15.74 -0.0177
|
||||
16.75 -0.0167
|
||||
17.75 -0.0147
|
||||
18.75 -0.0105
|
||||
19.74 -0.0066
|
||||
20.73 -0.0028
|
||||
|
||||
15
|
||||
-10.31 -0.0366
|
||||
-8.22 -0.0375
|
||||
-6.12 -0.0386
|
||||
-4.01 -0.0408
|
||||
-1.91 -0.04
|
||||
0.2 -0.0405
|
||||
2.29 -0.0424
|
||||
4.4 -0.0424
|
||||
6.5 -0.0422
|
||||
8.59 -0.0407
|
||||
10.65 -0.0382
|
||||
12.71 -0.0364
|
||||
13.72 -0.0332
|
||||
14.73 -0.0307
|
||||
15.74 -0.028
|
||||
16.75 -0.0267
|
||||
17.75 -0.0238
|
||||
18.75 -0.0179
|
||||
19.74 -0.013
|
||||
20.73 -0.0077
|
||||
|
||||
20
|
||||
-10.31 -0.0446
|
||||
-8.22 -0.0463
|
||||
-6.12 -0.0482
|
||||
-4.01 -0.0484
|
||||
-1.91 -0.0475
|
||||
0.2 -0.0482
|
||||
2.29 -0.0519
|
||||
4.4 -0.0519
|
||||
6.5 -0.0527
|
||||
8.59 -0.0521
|
||||
10.65 -0.0495
|
||||
12.71 -0.0466
|
||||
13.72 -0.0437
|
||||
14.73 -0.0411
|
||||
15.74 -0.0388
|
||||
16.75 -0.036
|
||||
17.75 -0.0333
|
||||
18.75 -0.0285
|
||||
19.74 -0.0226
|
||||
20.73 -0.017
|
||||
|
||||
25
|
||||
-10.31 -0.0533
|
||||
-8.22 -0.0553
|
||||
-6.12 -0.0568
|
||||
-4.01 -0.0563
|
||||
-1.91 -0.0568
|
||||
0.2 -0.0573
|
||||
2.29 -0.0604
|
||||
4.4 -0.0604
|
||||
6.5 -0.0614
|
||||
8.59 -0.0616
|
||||
10.65 -0.0597
|
||||
12.71 -0.0558
|
||||
13.72 -0.0524
|
||||
14.73 -0.0487
|
||||
15.74 -0.0461
|
||||
16.75 -0.0423
|
||||
17.75 -0.0376
|
||||
18.75 -0.0342
|
||||
19.74 -0.028
|
||||
20.73 -0.0229
|
||||
28
Aircraft-uiuc/Pioneer-TD/Cmfa.dat
Normal file
28
Aircraft-uiuc/Pioneer-TD/Cmfa.dat
Normal file
|
|
@ -0,0 +1,28 @@
|
|||
# Pioneer Cm as function of alpha [deg]
|
||||
|
||||
-8 0.411
|
||||
-7 0.39
|
||||
-6 0.365
|
||||
-5 0.338
|
||||
-4 0.309
|
||||
-3 0.279
|
||||
-2 0.251
|
||||
-1 0.222
|
||||
0 0.194
|
||||
1 0.167
|
||||
2 0.139
|
||||
3 0.11
|
||||
4 0.08
|
||||
5 0.047
|
||||
6 0.012
|
||||
7 -0.027
|
||||
8 -0.07
|
||||
9 -0.116
|
||||
10 -0.168
|
||||
11 -0.223
|
||||
12 -0.281
|
||||
13 -0.342
|
||||
14 -0.404
|
||||
15 -0.465
|
||||
16 -0.522
|
||||
17 -0.573
|
||||
201
Aircraft-uiuc/Pioneer-TD/Cmfade.dat
Normal file
201
Aircraft-uiuc/Pioneer-TD/Cmfade.dat
Normal file
|
|
@ -0,0 +1,201 @@
|
|||
# Pioneer change in Cm as function of alpha and elevator deflection
|
||||
|
||||
-25
|
||||
-6 0.9219
|
||||
-4 0.8735
|
||||
-2 0.827
|
||||
0 0.7798
|
||||
2 0.7413
|
||||
4 0.6706
|
||||
6 0.587
|
||||
8 0.5293
|
||||
10 0.4276
|
||||
12 0.3045
|
||||
13 0.2379
|
||||
14 0.1698
|
||||
15 0.1088
|
||||
16 0.0503
|
||||
17 -0.006
|
||||
18 -0.0704
|
||||
19 -0.1576
|
||||
20 -0.2624
|
||||
|
||||
-20
|
||||
-6 0.8532
|
||||
-4 0.8031
|
||||
-2 0.7546
|
||||
0 0.7073
|
||||
2 0.6698
|
||||
4 0.5983
|
||||
6 0.5275
|
||||
8 0.4822
|
||||
10 0.3743
|
||||
12 0.252
|
||||
13 0.1943
|
||||
14 0.1367
|
||||
15 0.0721
|
||||
16 0.0109
|
||||
17 -0.0452
|
||||
18 -0.1072
|
||||
19 -0.1668
|
||||
20 -0.2034
|
||||
|
||||
-15
|
||||
-6 0.7722
|
||||
-4 0.7138
|
||||
-2 0.6717
|
||||
0 0.6258
|
||||
2 0.5939
|
||||
4 0.5384
|
||||
6 0.4621
|
||||
8 0.4109
|
||||
10 0.3178
|
||||
12 0.2058
|
||||
13 0.1426
|
||||
14 0.0705
|
||||
15 0.0028
|
||||
16 -0.0594
|
||||
17 -0.123
|
||||
18 -0.1827
|
||||
19 -0.2384
|
||||
20 -0.2822
|
||||
|
||||
-10
|
||||
-6 0.6464
|
||||
-4 0.5998
|
||||
-2 0.559
|
||||
0 0.5156
|
||||
2 0.4682
|
||||
4 0.4039
|
||||
6 0.3265
|
||||
8 0.2551
|
||||
10 0.1513
|
||||
12 0.0404
|
||||
13 -0.0216
|
||||
14 -0.0911
|
||||
15 -0.1512
|
||||
16 -0.2198
|
||||
17 -0.2834
|
||||
18 -0.3425
|
||||
19 -0.3938
|
||||
20 -0.4234
|
||||
|
||||
-5
|
||||
-6 0.5099
|
||||
-4 0.4673
|
||||
-2 0.4248
|
||||
0 0.3705
|
||||
2 0.3111
|
||||
4 0.2426
|
||||
6 0.1675
|
||||
8 0.0901
|
||||
10 -0.0115
|
||||
12 -0.1199
|
||||
13 -0.1775
|
||||
14 -0.2419
|
||||
15 -0.3048
|
||||
16 -0.3693
|
||||
17 -0.429
|
||||
18 -0.4869
|
||||
19 -0.5246
|
||||
20 -0.5369
|
||||
|
||||
0
|
||||
-6 0.3524
|
||||
-4 0.305
|
||||
-2 0.2505
|
||||
0 0.1922
|
||||
2 0.1331
|
||||
4 0.0681
|
||||
6 -0.0041
|
||||
8 -0.0826
|
||||
10 -0.1771
|
||||
12 -0.285
|
||||
13 -0.3435
|
||||
14 -0.4058
|
||||
15 -0.4655
|
||||
16 -0.5284
|
||||
17 -0.583
|
||||
18 -0.626
|
||||
19 -0.6414
|
||||
20 -0.6366
|
||||
|
||||
5
|
||||
-6 0.2042
|
||||
-4 0.1561
|
||||
-2 0.1051
|
||||
0 0.0403
|
||||
2 -0.0198
|
||||
4 -0.0833
|
||||
6 -0.1556
|
||||
8 -0.2472
|
||||
10 -0.3376
|
||||
12 -0.4361
|
||||
13 -0.4882
|
||||
14 -0.5455
|
||||
15 -0.6097
|
||||
16 -0.6657
|
||||
17 -0.7117
|
||||
18 -0.7409
|
||||
19 -0.7367
|
||||
20 -0.726
|
||||
|
||||
10
|
||||
-6 0.0376
|
||||
-4 -0.0146
|
||||
-2 -0.075
|
||||
0 -0.1391
|
||||
2 -0.1921
|
||||
4 -0.2594
|
||||
6 -0.3327
|
||||
8 -0.4179
|
||||
10 -0.5038
|
||||
12 -0.5937
|
||||
13 -0.6446
|
||||
14 -0.7024
|
||||
15 -0.7536
|
||||
16 -0.8052
|
||||
17 -0.8406
|
||||
18 -0.8481
|
||||
19 -0.832
|
||||
20 -0.8175
|
||||
|
||||
15
|
||||
-6 -0.11
|
||||
-4 -0.1606
|
||||
-2 -0.2137
|
||||
0 -0.2678
|
||||
2 -0.3162
|
||||
4 -0.378
|
||||
6 -0.4518
|
||||
8 -0.5384
|
||||
10 -0.6162
|
||||
12 -0.6994
|
||||
13 -0.7465
|
||||
14 -0.8015
|
||||
15 -0.8507
|
||||
16 -0.903
|
||||
17 -0.9229
|
||||
18 -0.9051
|
||||
19 -0.8863
|
||||
20 -0.8832
|
||||
|
||||
20
|
||||
-6 -0.1353
|
||||
-4 -0.1817
|
||||
-2 -0.2356
|
||||
0 -0.3001
|
||||
2 -0.3675
|
||||
4 -0.4532
|
||||
6 -0.5296
|
||||
8 -0.6121
|
||||
10 -0.6925
|
||||
12 -0.7772
|
||||
13 -0.8266
|
||||
14 -0.8897
|
||||
15 -0.9399
|
||||
16 -0.9818
|
||||
17 -0.9877
|
||||
18 -0.9575
|
||||
19 -0.9439
|
||||
20 -0.9447
|
||||
197
Aircraft-uiuc/Pioneer-TD/Cnfada.dat
Normal file
197
Aircraft-uiuc/Pioneer-TD/Cnfada.dat
Normal file
|
|
@ -0,0 +1,197 @@
|
|||
# Pioneer change in Cn as function of alpha and aileron deflection
|
||||
|
||||
5
|
||||
-8 -0.0004
|
||||
-7 -0.0002
|
||||
-6 -0.0001
|
||||
-5 0.0001
|
||||
-4 0.0002
|
||||
-3 0.0004
|
||||
-2 0.0005
|
||||
-1 0.0007
|
||||
0 0.0008
|
||||
1 0.001
|
||||
2 0.0011
|
||||
3 0.0013
|
||||
4 0.0015
|
||||
5 0.0016
|
||||
6 0.0018
|
||||
7 0.0019
|
||||
8 0.0021
|
||||
9 0.0022
|
||||
10 0.0024
|
||||
11 0.0026
|
||||
12 0.0027
|
||||
13 0.0029
|
||||
14 0.003
|
||||
15 0.0032
|
||||
16 0.0034
|
||||
17 0.0035
|
||||
|
||||
0
|
||||
-8 0
|
||||
-7 0
|
||||
-6 0
|
||||
-5 0
|
||||
-4 0
|
||||
-3 0
|
||||
-2 0
|
||||
-1 0
|
||||
0 0
|
||||
1 0
|
||||
2 0
|
||||
3 0
|
||||
4 0
|
||||
5 0
|
||||
6 0
|
||||
7 0
|
||||
8 0
|
||||
9 0
|
||||
10 0
|
||||
11 0
|
||||
12 0
|
||||
13 0
|
||||
14 0
|
||||
15 0
|
||||
16 0
|
||||
17 0
|
||||
|
||||
5
|
||||
-8 0.0004
|
||||
-7 0.0002
|
||||
-6 0.0001
|
||||
-5 -0.0001
|
||||
-4 -0.0002
|
||||
-3 -0.0004
|
||||
-2 -0.0005
|
||||
-1 -0.0007
|
||||
0 -0.0008
|
||||
1 -0.001
|
||||
2 -0.0011
|
||||
3 -0.0013
|
||||
4 -0.0015
|
||||
5 -0.0016
|
||||
6 -0.0018
|
||||
7 -0.0019
|
||||
8 -0.0021
|
||||
9 -0.0022
|
||||
10 -0.0024
|
||||
11 -0.0026
|
||||
12 -0.0027
|
||||
13 -0.0029
|
||||
14 -0.003
|
||||
15 -0.0032
|
||||
16 -0.0034
|
||||
17 -0.0035
|
||||
|
||||
10
|
||||
-8 0.0013
|
||||
-7 0.0009
|
||||
-6 0.0004
|
||||
-5 0
|
||||
-4 -0.0004
|
||||
-3 -0.0007
|
||||
-2 -0.0011
|
||||
-1 -0.0015
|
||||
0 -0.0018
|
||||
1 -0.0022
|
||||
2 -0.0025
|
||||
3 -0.0029
|
||||
4 -0.0032
|
||||
5 -0.0035
|
||||
6 -0.0038
|
||||
7 -0.0041
|
||||
8 -0.0043
|
||||
9 -0.0046
|
||||
10 -0.0049
|
||||
11 -0.0051
|
||||
12 -0.0054
|
||||
13 -0.0056
|
||||
14 -0.0058
|
||||
15 -0.006
|
||||
16 -0.0062
|
||||
17 -0.0064
|
||||
|
||||
15
|
||||
-8 0.0014
|
||||
-7 0.0008
|
||||
-6 0.0003
|
||||
-5 -0.0002
|
||||
-4 -0.0007
|
||||
-3 -0.0011
|
||||
-2 -0.0016
|
||||
-1 -0.0021
|
||||
0 -0.0026
|
||||
1 -0.003
|
||||
2 -0.0035
|
||||
3 -0.004
|
||||
4 -0.0044
|
||||
5 -0.0049
|
||||
6 -0.0053
|
||||
7 -0.0057
|
||||
8 -0.0062
|
||||
9 -0.0066
|
||||
10 -0.007
|
||||
11 -0.0074
|
||||
12 -0.0078
|
||||
13 -0.0082
|
||||
14 -0.0086
|
||||
15 -0.009
|
||||
16 -0.0094
|
||||
17 -0.0098
|
||||
|
||||
20
|
||||
-8 0.0022
|
||||
-7 0.0015
|
||||
-6 0.0008
|
||||
-5 0.0001
|
||||
-4 -0.0005
|
||||
-3 -0.0012
|
||||
-2 -0.0019
|
||||
-1 -0.0025
|
||||
0 -0.0032
|
||||
1 -0.0038
|
||||
2 -0.0044
|
||||
3 -0.005
|
||||
4 -0.0057
|
||||
5 -0.0063
|
||||
6 -0.0069
|
||||
7 -0.0075
|
||||
8 -0.0081
|
||||
9 -0.0087
|
||||
10 -0.0093
|
||||
11 -0.0098
|
||||
12 -0.0104
|
||||
13 -0.011
|
||||
14 -0.0115
|
||||
15 -0.0121
|
||||
16 -0.0126
|
||||
17 -0.0132
|
||||
|
||||
25
|
||||
-8 0.0025
|
||||
-7 0.0018
|
||||
-6 0.001
|
||||
-5 0.0003
|
||||
-4 -0.0004
|
||||
-3 -0.0012
|
||||
-2 -0.0019
|
||||
-1 -0.0026
|
||||
0 -0.0033
|
||||
1 -0.004
|
||||
2 -0.0047
|
||||
3 -0.0054
|
||||
4 -0.0061
|
||||
5 -0.0068
|
||||
6 -0.0074
|
||||
7 -0.0081
|
||||
8 -0.0088
|
||||
9 -0.0094
|
||||
10 -0.0101
|
||||
11 -0.0107
|
||||
12 -0.0114
|
||||
13 -0.012
|
||||
14 -0.0127
|
||||
15 -0.0133
|
||||
16 -0.0139
|
||||
17 -0.0145
|
||||
254
Aircraft-uiuc/Pioneer-TD/Cnfbetadr.dat
Normal file
254
Aircraft-uiuc/Pioneer-TD/Cnfbetadr.dat
Normal file
|
|
@ -0,0 +1,254 @@
|
|||
# Pioneer change in Cn as function of beta and rudder deflection
|
||||
|
||||
-25
|
||||
-20 0.0067
|
||||
-17.5 0
|
||||
-15 0.004
|
||||
-12.5 0.0087
|
||||
-10 0.0121
|
||||
-7.5 0.0161
|
||||
-5 0.02
|
||||
-2.5 0.0275
|
||||
0 0.0335
|
||||
2.5 0.0382
|
||||
5 0.0429
|
||||
7.5 0.0476
|
||||
10 0.0516
|
||||
11.25 0.0549
|
||||
12.5 0.0563
|
||||
13.75 0.057
|
||||
15 0.0523
|
||||
16.25 0.0503
|
||||
17.5 0.0509
|
||||
18.75 0.0509
|
||||
20 0.0509
|
||||
|
||||
-20
|
||||
-20 0.0027
|
||||
-17.5 0.0013
|
||||
-15 0.002
|
||||
-12.5 0.0074
|
||||
-10 0.0101
|
||||
-7.5 0.0127
|
||||
-5 0.0174
|
||||
-2.5 0.0235
|
||||
0 0.0295
|
||||
2.5 0.0348
|
||||
5 0.0389
|
||||
7.5 0.0429
|
||||
10 0.0462
|
||||
11.25 0.0489
|
||||
12.5 0.0509
|
||||
13.75 0.0509
|
||||
15 0.0482
|
||||
16.25 0.0442
|
||||
17.5 0.0428
|
||||
18.75 0.0436
|
||||
20 0.0442
|
||||
|
||||
-15
|
||||
-20 -0.0027
|
||||
-17.5 -0.0054
|
||||
-15 -0.004
|
||||
-12.5 0.0027
|
||||
-10 0.0054
|
||||
-7.5 0.0087
|
||||
-5 0.0134
|
||||
-2.5 0.0188
|
||||
0 0.0255
|
||||
2.5 0.0288
|
||||
5 0.0328
|
||||
7.5 0.0375
|
||||
10 0.0422
|
||||
11.25 0.0442
|
||||
12.5 0.0462
|
||||
13.75 0.0469
|
||||
15 0.0429
|
||||
16.25 0.0415
|
||||
17.5 0.0422
|
||||
18.75 0.0429
|
||||
20 0.0429
|
||||
|
||||
-10
|
||||
-20 -0.0094
|
||||
-17.5 -0.0127
|
||||
-15 -0.0114
|
||||
-12.5 -0.0047
|
||||
-10 -0.0014
|
||||
-7.5 0.0013
|
||||
-5 0.0067
|
||||
-2.5 0.0127
|
||||
0 0.0188
|
||||
2.5 0.0228
|
||||
5 0.0261
|
||||
7.5 0.0288
|
||||
10 0.0348
|
||||
11.25 0.0375
|
||||
12.5 0.0395
|
||||
13.75 0.0402
|
||||
15 0.0369
|
||||
16.25 0.0355
|
||||
17.5 0.0355
|
||||
18.75 0.0362
|
||||
20 0.0369
|
||||
|
||||
-5
|
||||
-20 -0.0154
|
||||
-17.5 -0.0214
|
||||
-15 -0.02
|
||||
-12.5 -0.0134
|
||||
-10 -0.0101
|
||||
-7.5 -0.0064
|
||||
-5 -0.002
|
||||
-2.5 0.0047
|
||||
0 0.0114
|
||||
2.5 0.0154
|
||||
5 0.0121
|
||||
7.5 0.0248
|
||||
10 0.0295
|
||||
11.25 0.0315
|
||||
12.5 0.0335
|
||||
13.75 0.0342
|
||||
15 0.0322
|
||||
16.25 0.0308
|
||||
17.5 0.0308
|
||||
18.75 0.0308
|
||||
20 0.0322
|
||||
|
||||
0
|
||||
-20 -0.0214
|
||||
-17.5 -0.0277
|
||||
-15 -0.0283
|
||||
-12.5 -0.0222
|
||||
-10 -0.0188
|
||||
-7.5 -0.0161
|
||||
-5 -0.0131
|
||||
-2.5 -0.0067
|
||||
0 0
|
||||
2.5 0.006
|
||||
5 0.0101
|
||||
7.5 0.0154
|
||||
10 0.0188
|
||||
11.25 0.0201
|
||||
12.5 0.0235
|
||||
13.75 0.0268
|
||||
15 0.0255
|
||||
16.25 0.0255
|
||||
17.5 0.0235
|
||||
18.75 0.0235
|
||||
20 0.0248
|
||||
|
||||
5
|
||||
-20 -0.0274
|
||||
-17.5 -0.034
|
||||
-15 -0.0366
|
||||
-12.5 -0.031
|
||||
-10 -0.0275
|
||||
-7.5 -0.0258
|
||||
-5 -0.0242
|
||||
-2.5 -0.0181
|
||||
0 -0.0074
|
||||
2.5 -0.0034
|
||||
5 0.0081
|
||||
7.5 0.006
|
||||
10 0.0081
|
||||
11.25 0.0087
|
||||
12.5 0.0135
|
||||
13.75 0.0194
|
||||
15 0.0188
|
||||
16.25 0.0202
|
||||
17.5 0.0162
|
||||
18.75 0.0162
|
||||
20 0.0174
|
||||
|
||||
10
|
||||
-20 -0.0334
|
||||
-17.5 -0.0427
|
||||
-15 -0.0452
|
||||
-12.5 -0.0397
|
||||
-10 -0.0362
|
||||
-7.5 -0.0335
|
||||
-5 -0.0329
|
||||
-2.5 -0.0261
|
||||
0 -0.0148
|
||||
2.5 -0.0108
|
||||
5 -0.0059
|
||||
7.5 0.002
|
||||
10 0.0028
|
||||
11.25 0.0027
|
||||
12.5 0.0075
|
||||
13.75 0.0134
|
||||
15 0.0141
|
||||
16.25 0.0155
|
||||
17.5 0.0115
|
||||
18.75 0.0108
|
||||
20 0.0127
|
||||
|
||||
15
|
||||
-20 -0.0401
|
||||
-17.5 -0.05
|
||||
-15 -0.0526
|
||||
-12.5 -0.0471
|
||||
-10 -0.043
|
||||
-7.5 -0.0409
|
||||
-5 -0.0396
|
||||
-2.5 -0.0322
|
||||
0 -0.0215
|
||||
2.5 -0.0168
|
||||
5 -0.0126
|
||||
7.5 -0.0067
|
||||
10 -0.0046
|
||||
11.25 -0.004
|
||||
12.5 0.0008
|
||||
13.75 0.0067
|
||||
15 0.0081
|
||||
16.25 0.0095
|
||||
17.5 0.0048
|
||||
18.75 0.0041
|
||||
20 0.0067
|
||||
|
||||
20
|
||||
-20 -0.0455
|
||||
-17.5 -0.0567
|
||||
-15 -0.586
|
||||
-12.5 -0.0052
|
||||
-10 -0.0477
|
||||
-7.5 -0.0449
|
||||
-5 -0.0436
|
||||
-2.5 -0.0369
|
||||
0 -0.0255
|
||||
2.5 -0.0228
|
||||
5 -0.0187
|
||||
7.5 -0.0121
|
||||
10 -0.0086
|
||||
11.25 -0.0088
|
||||
12.5 -0.0039
|
||||
13.75 0.0027
|
||||
15 0.0001
|
||||
16.25 0.0068
|
||||
17.5 0.0042
|
||||
18.75 0.0034
|
||||
20 0.0054
|
||||
|
||||
25
|
||||
-20 -0.0495
|
||||
-17.5 -0.0554
|
||||
-15 -0.0606
|
||||
-12.5 -0.0531
|
||||
-10 -0.0497
|
||||
-7.5 -0.0483
|
||||
-5 -0.0462
|
||||
-2.5 -0.0409
|
||||
0 -0.0295
|
||||
2.5 -0.0262
|
||||
5 -0.0227
|
||||
7.5 -0.0168
|
||||
10 -0.014
|
||||
11.25 -0.0147
|
||||
12.5 -0.0093
|
||||
13.75 -0.0034
|
||||
15 -0.0013
|
||||
16.25 0.0007
|
||||
17.5 -0.0039
|
||||
18.75 -0.0039
|
||||
20 -0.0013
|
||||
106
Aircraft-uiuc/Pioneer-TD/aircraft.dat
Normal file
106
Aircraft-uiuc/Pioneer-TD/aircraft.dat
Normal file
|
|
@ -0,0 +1,106 @@
|
|||
# Jeff Scott
|
||||
# IAI Pioneer
|
||||
# single piston engine unmanned aircraft (UAV)
|
||||
# This model was generated from wind tunnel tests done on a full
|
||||
# scale model of the Pioneer UAV. This version of the Pioneer
|
||||
# utilizes tabulated data. Data is taken from
|
||||
# Bray, Robert M. A Wind Tunnel Investigation of the Pioneer
|
||||
# Remotely Piloted Vehicle. Montery, CA: Naval
|
||||
# Postgraduate School, June 1991.
|
||||
# Selig, Michael S. Pioneer aircraft notes.
|
||||
# 01-25-2000 file creation
|
||||
# 03-23-2000 corrected sign error on Cn_r
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
|
||||
geometry bw 16.90 # [ft] Bray pg 31
|
||||
geometry cbar 1.80 # [ft] Bray pg 31
|
||||
geometry Sw 30.42 # [ft^2] Bray pg 31
|
||||
#geometry iw 3 # [deg] Bray pg 31
|
||||
#geometry bh 6.07 # [ft] Bray pg 31
|
||||
#geometry ch 1.0 # [ft] Bray pg 31
|
||||
#geometry Sh 6.07 # [sq-ft] Bray pg 31
|
||||
#geometry ih -3 # [deg] Bray pg 31
|
||||
#geometry bv 2.17 # [ft] Bray pg 31
|
||||
#geometry cv 6.07 # [ft] Bray pg 31
|
||||
#geometry Sv 2.17 # [ft^2] Bray pg 31
|
||||
|
||||
controlSurface de 20 20 # [deg] Bray pg 31
|
||||
controlSurface da 20 20 # [deg] Bray pg 31
|
||||
controlSurface dr 20 20 # [deg] Bray pg 31
|
||||
#controlSurface df <dfmax> <dfmin> # [deg]
|
||||
|
||||
mass Weight 420 # [lb] Bray pg 33
|
||||
mass I_xx 34.832 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_yy 67.08 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_zz 82.22 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_xz -4.902 # [slug-ft^2] IAI, MSS notes
|
||||
|
||||
|
||||
# aircraft specs: 27 hp
|
||||
# ~100 lb static thrust
|
||||
engine simpleSingle 100 # [lb] guess
|
||||
|
||||
|
||||
#CL CLo 0.385 # [] Bray pg 33
|
||||
#CL CL_a 4.78 # [/rad] Bray pg 33
|
||||
CL CL_adot 2.42 # [/rad] Bray pg 33
|
||||
CL CL_q 8.05 # [/rad] Bray pg 33
|
||||
#CL CL_de 0.401 # [/rad] Bray pg 33
|
||||
CL CLfa Aircraft-uiuc/Pioneer-TD/CLfa.dat 0 1 # Bray pg 50, Table 4.7
|
||||
CL CLfade Aircraft-uiuc/Pioneer-TD/CLfade.dat 0 1 1 # Bray pg 41, Table 4.4
|
||||
|
||||
#CD CDo 0.060 # [] Bray pg 33
|
||||
#CD CD_a 0.430 # [/rad] Bray pg 33
|
||||
#CD CD_de 0.0180 # [/rad] Bray pg 33
|
||||
CD CDfa Aircraft-uiuc/Pioneer-TD/CDfa.dat 0 1 # Bray pg 50, Table 4.7
|
||||
CD CDfade Aircraft-uiuc/Pioneer-TD/CDfade.dat 0 1 1 # Bray pg 45, Table 4.6
|
||||
|
||||
#Cm Cmo 0.194 # [] Bray pg 33
|
||||
#Cm Cm_a -2.12 # [/rad] Bray pg 33
|
||||
Cm Cm_adot -11.0 # [/rad] Bray pg 33
|
||||
Cm Cm_q -36.6 # [/rad] Bray pg 33
|
||||
#Cm Cm_de -1.76 # [/rad] Bray pg 33
|
||||
Cm Cmfa Aircraft-uiuc/Pioneer-TD/Cmfa.dat 0 1 # Bray pg 50, Table 4.7
|
||||
Cm Cmfade Aircraft-uiuc/Pioneer-TD/Cmfade.dat 0 1 1 # Bray pg 34, Figure 4.2
|
||||
|
||||
CY CY_beta -0.819 # [/rad] Bray pg 33
|
||||
#CY CY_p <CY_p> # [/rad] no data
|
||||
#CY CY_r <CY_r> # [/rad] no data
|
||||
#CY CY_da <CY_da> # [/rad] no data
|
||||
#CY CY_dr 0.191 # [/rad] Bray pg 33
|
||||
#CY CYfada <CYfada.dat> # [] no data
|
||||
CY CYfbetadr Aircraft-uiuc/Pioneer-TD/CYfbetadr.dat 0 1 1 # Bray pg 62, Figure 4.19
|
||||
|
||||
Cl Cl_beta -0.023 # [/rad] Bray pg 33
|
||||
Cl Cl_p -0.450 # [/rad] Bray pg 33
|
||||
Cl Cl_r 0.265 # [/rad] Bray pg 33
|
||||
#Cl Cl_da -0.161 # [/rad] Bray pg 33 (sign reversed)
|
||||
Cl Cl_dr -0.00229 # [/rad] Bray pg 33
|
||||
Cl Clfada Aircraft-uiuc/Pioneer-TD/Clfada.dat 0 1 1 # Bray pg 58, Table 4.8
|
||||
|
||||
Cn Cn_beta 0.109 # [/rad] Bray pg 33
|
||||
Cn Cn_p -0.110 # [/rad] Bray pg 33
|
||||
Cn Cn_r -0.200 # [/rad] Bray pg 33
|
||||
#Cn Cn_da 0.0200 # [/rad] Bray pg 33 (sign reversed)
|
||||
#Cn Cn_dr -0.0917 # [/rad] Bray pg 33
|
||||
Cn Cnfada Aircraft-uiuc/Pioneer-TD/Cnfada.dat 0 1 1 # Bray pg 61, Table 4.9
|
||||
Cn Cnfbetadr Aircraft-uiuc/Pioneer-TD/Cnfbetadr.dat 0 1 1 # Bray pg 63, Figure 4.20
|
||||
|
||||
*
|
||||
|
||||
record Alpha
|
||||
record CDfaI
|
||||
record CLfaI
|
||||
record CmfaI
|
||||
record elevator
|
||||
record CDfadeI
|
||||
record CLfadeI
|
||||
record CmfadeI
|
||||
record aileron
|
||||
record ClfadaI
|
||||
record CnfadaI
|
||||
record Beta
|
||||
record rudder
|
||||
record CYfbetadrI
|
||||
record CnfbetadrI
|
||||
86
Aircraft-uiuc/Pioneer/aircraft.dat
Normal file
86
Aircraft-uiuc/Pioneer/aircraft.dat
Normal file
|
|
@ -0,0 +1,86 @@
|
|||
# Jeff Scott
|
||||
# IAI Pioneer
|
||||
# single piston engine unmanned aircraft (UAV)
|
||||
# This model was generated from wind tunnel tests done on a full
|
||||
# scale model of the Pioneer UAV. This version of the Pioneer
|
||||
# utilizes stability derivatives (all constants). Data is taken from
|
||||
# Bray, Robert M. A Wind Tunnel Investigation of the Pioneer
|
||||
# Remotely Piloted Vehicle. Montery, CA: Naval
|
||||
# Postgraduate School, June 1991.
|
||||
# Selig, Michael S. Pioneer aircraft notes.
|
||||
# 01-25-2000 file creation
|
||||
# 03-23-2000 corrected sign error on Cn_r
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
|
||||
geometry bw 16.90 # [ft] Bray pg 31
|
||||
geometry cbar 1.80 # [ft] Bray pg 31
|
||||
geometry Sw 30.42 # [ft^2] Bray pg 31
|
||||
#geometry iw 3 # [deg] Bray pg 31
|
||||
#geometry bh 6.07 # [ft] Bray pg 31
|
||||
#geometry ch 1.0 # [ft] Bray pg 31
|
||||
#geometry Sh 6.07 # [sq-ft] Bray pg 31
|
||||
#geometry ih -3 # [deg] Bray pg 31
|
||||
#geometry bv 2.17 # [ft] Bray pg 31
|
||||
#geometry cv 6.07 # [ft] Bray pg 31
|
||||
#geometry Sv 2.17 # [ft^2] Bray pg 31
|
||||
|
||||
controlSurface de 20 20 # [deg] Bray pg 31
|
||||
controlSurface da 20 20 # [deg] Bray pg 31
|
||||
controlSurface dr 20 20 # [deg] Bray pg 31
|
||||
|
||||
mass Weight 420 # [lb] Bray pg 33
|
||||
mass I_xx 34.832 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_yy 67.08 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_zz 82.22 # [slug-ft^2] IAI, MSS notes
|
||||
mass I_xz -4.902 # [slug-ft^2] IAI, MSS notes
|
||||
|
||||
|
||||
# aircraft specs: 27 hp
|
||||
# ~100 lb static thrust
|
||||
engine simpleSingle 100 # [lb] guess
|
||||
|
||||
|
||||
CL CLo 0.385 # [] Bray pg 33
|
||||
CL CL_a 4.78 # [/rad] Bray pg 33
|
||||
CL CL_adot 2.42 # [/rad] Bray pg 33
|
||||
CL CL_q 8.05 # [/rad] Bray pg 33
|
||||
CL CL_de 0.401 # [/rad] Bray pg 33
|
||||
#CL CLfa CLfa.dat 0 1 # Bray pg 50, Table 4.7
|
||||
#CL CLfade CLfade.dat 0 1 1 # Bray pg 41, Table 4.4
|
||||
|
||||
CD CDo 0.060 # [] Bray pg 33
|
||||
CD CD_a 0.430 # [/rad] Bray pg 33
|
||||
CD CD_de 0.0180 # [/rad] Bray pg 33
|
||||
#CD CDfa Cdfa.dat 0 1 # Bray pg 50, Table 4.7
|
||||
#CD CDfade CDfade.dat 0 1 1 # Bray pg 45, Table 4.6
|
||||
|
||||
Cm Cmo 0.194 # [] Bray pg 33
|
||||
Cm Cm_a -2.12 # [/rad] Bray pg 33
|
||||
Cm Cm_adot -11.0 # [/rad] Bray pg 33
|
||||
Cm Cm_q -36.6 # [/rad] Bray pg 33
|
||||
Cm Cm_de -1.76 # [/rad] Bray pg 33
|
||||
#Cm Cmfade Cmfade.dat 0 1 1 # Bray pg 34, Figure 4.2
|
||||
|
||||
CY CY_beta -0.819 # [/rad] Bray pg 33
|
||||
#CY CY_p <CY_p> # [/rad] no data
|
||||
#CY CY_r <CY_r> # [/rad] no data
|
||||
#CY CY_da <CY_da> # [/rad] no data
|
||||
CY CY_dr 0.191 # [/rad] Bray pg 33
|
||||
#CY CYfada <CYfada.dat> # [] no data
|
||||
#CY CYfbetadr CYfbetadr.dat 0 1 1 # [] Bray pg 62, Figure 4.19
|
||||
|
||||
Cl Cl_beta -0.023 # [/rad] Bray pg 33
|
||||
Cl Cl_p -0.450 # [/rad] Bray pg 33
|
||||
Cl Cl_r 0.265 # [/rad] Bray pg 33
|
||||
Cl Cl_da -0.161 # [/rad] Bray pg 33 (sign reversed)
|
||||
Cl Cl_dr -0.00229 # [/rad] Bray pg 33
|
||||
#Cl Clfada Clfada.dat 0 1 1 # Bray pg 58, Table 4.8
|
||||
|
||||
Cn Cn_beta 0.109 # [/rad] Bray pg 33
|
||||
Cn Cn_p -0.110 # [/rad] Bray pg 33
|
||||
Cn Cn_r -0.200 # [/rad] Bray pg 33
|
||||
Cn Cn_da 0.0200 # [/rad] Bray pg 33 (sign reversed)
|
||||
Cn Cn_dr -0.0917 # [/rad] Bray pg 33
|
||||
#Cn Cnfada Cnfada.dat 0 1 1 # Bray pg 61, Table 4.9
|
||||
#Cn Cnfbetadr Cnfbetadr.dat 0 1 1 # Bray pg 63, Figure 4.20
|
||||
204
Aircraft-uiuc/README-aircraft-uiuc.html
Normal file
204
Aircraft-uiuc/README-aircraft-uiuc.html
Normal file
|
|
@ -0,0 +1,204 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>UIUC Aircraft Models</title>
|
||||
</head>
|
||||
<body>
|
||||
|
||||
<pre>
|
||||
************************************************
|
||||
* *
|
||||
* FGFS Reconfigurable Aircraft Flight Model *
|
||||
* Sample Input Files *
|
||||
* Version 0.73, June 27, 2000 *
|
||||
* *
|
||||
* Authors: *
|
||||
* Jeff Scott (jscott@mail.com) *
|
||||
* Bipin Sehgal (bsehgal@uiuc.edu) *
|
||||
* Michael Selig (m-selig@uiuc.edu) *
|
||||
* Dept of Aero and Astro Engineering *
|
||||
* University of Illinois at Urbana-Champaign *
|
||||
* Urbana, IL *
|
||||
* http://amber.aae.uiuc.edu/~m-selig *
|
||||
* *
|
||||
************************************************
|
||||
|
||||
The simulator executable, fgfs.exe, uses the aircraft.dat files
|
||||
located in Aircraft-uiuc to fly the desired aircraft. This file
|
||||
should either be in the same directory as fgfs.exe or should be called
|
||||
from the command line. To do the latter, open a DOS or Cygwin shell
|
||||
and go to the directory containing fgfs.exe. Type the following:
|
||||
|
||||
> fgfs.exe --aircraft-dir=Aircraft-uiuc/Cessna172
|
||||
|
||||
The same procedure can be accomplished using a batch file. A sample
|
||||
batch file (runfgfs.bat) is provided in the top level directory. To
|
||||
run the desired aircraft, simply delete the "rem" command from the
|
||||
beginning of the line. Make sure that all the other model lines still
|
||||
begin with "rem" or you may not actually be flying the plane you
|
||||
want. Double click the file runfgfs.bat to begin the simulation.
|
||||
|
||||
There is also a record feature that generates a file called
|
||||
uiuc_record.dat. The desired variables can be recorded in this file
|
||||
using the proper record lines. The syntax of these lines and the
|
||||
aircraft.dat files in general is provided in the documentation file
|
||||
<a href="README-uiucDoc.txt">README-uiucDoc.txt</a>.
|
||||
|
||||
The runfgfs.bat file also provides samples of other command line
|
||||
options, including time of day, cloud and fog options, and the airport
|
||||
from which the flight begins. The airport commands are provided in
|
||||
<a href="README-airports.html">README-airports.html</a>. An overview
|
||||
of all the options available for the command line is provided in
|
||||
<a href="README-options.html">README-options.html</a>.
|
||||
|
||||
Note that the proper scenery for that segment of the world must be
|
||||
provided for the scenery at that airport to be rendered. If the
|
||||
desired airport is not available (i.e. you see a bluish terrain when
|
||||
the program begins), you will need to download the additional terrain
|
||||
at <a href="http://www.flightgear.org/Downloads/world-scenery.html">
|
||||
http://www.flightgear.org/Downloads/world-scenery.html</a>.
|
||||
Simply click on the grid containing the desired airport, save to your
|
||||
computer and unzip the file to the Scenery directory. Note that the
|
||||
scenery files are very large and occupy a large amount of disk space!
|
||||
|
||||
|
||||
Notes:
|
||||
------
|
||||
|
||||
- All aircraft use the C172 gear model, and this gets overloaded for
|
||||
some of the heavier aircraft. Adding throttle will eventually lead
|
||||
to enough airspeed to fly. Once airborne, some corrective control
|
||||
inputs may be necessary.
|
||||
|
||||
- For each aircraft, the thrust was set to give more or less
|
||||
"reasonable" performance characteristics. Users are encouraged to
|
||||
vary the thrust (see line
|
||||
> engine simpleSingle [simpleSingleMaxThrust]
|
||||
and change the value) to improve performance.
|
||||
|
||||
- Most aircraft are modeled using cruise condition data only. Takeoff
|
||||
and landing configurations and associated changes in aerodynamic
|
||||
characteristics are not currently modeled.
|
||||
|
||||
- Some files use "record" lines to produce flight-data recorder
|
||||
output. These data are written to the file uiuc_record.dat. Be
|
||||
aware that when flying for an extended period of time this file (if
|
||||
written by using record lines) can become very large.
|
||||
|
||||
To fly, use one of the aircraft.dat files.
|
||||
The aircraft data used in each of these models is provided in the
|
||||
<a href="Aircraft-uiuc/models/index.html">Simulation Specifications</a>.
|
||||
Note that these models may be updated, revised, or extended. For the
|
||||
most recent versions, be sure to visit the on-line
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/models/">version</a>.
|
||||
|
||||
Beech99:
|
||||
Beech 99, small commercial commuter aircraft
|
||||
very smooth characteristics
|
||||
|
||||
Boeing747:
|
||||
Boeing 747, large commercial jetliner
|
||||
too heavy for gear so noses down into ground at 70 degree angle, but
|
||||
this can be fixed by going to max throttle till plane rotates and
|
||||
becomes airborne; sluggish, but flies well
|
||||
|
||||
Cessna172:
|
||||
Cessna 172, small general aviation aircraft
|
||||
based on Tony Peden's model, but uses stability derivatives only
|
||||
flies very well
|
||||
|
||||
Cessna172-TD:
|
||||
Cessna 172, small general aviation aircraft
|
||||
uses lift curve data from Peden model to model stall
|
||||
also flies well
|
||||
|
||||
Cessna310:
|
||||
Cessna 310, twin engine general aviation aircraft
|
||||
elevator seems too effective and slight instability in roll
|
||||
|
||||
Cessna620:
|
||||
Cessna 620, four engine business aircraft
|
||||
very sluggish
|
||||
|
||||
Convair880:
|
||||
Convair 880, medium commercial jetliner
|
||||
too heavy for gear so noses down into ground, but this can be fixed
|
||||
by going to max throttle till plane rotates and becomes airborne;
|
||||
play with the controls to obtain the proper orientation; sluggish,
|
||||
but flies pretty well
|
||||
*This model works best already in flight. The example in
|
||||
runfgfs.bat begins at 35,000 ft. To fly, increase the throttle and
|
||||
use small elevator and aileron deflections to level the aircraft.
|
||||
|
||||
F104:
|
||||
Lockheed F-104, small supersonic fighter
|
||||
flies pretty smoothly but it's called "the Widow maker" for a reason
|
||||
|
||||
F4:
|
||||
McDonnell F-4 Phantom, fighter/attack plane
|
||||
very difficult to fly and sometimes will have problems taking off
|
||||
from the ground
|
||||
*This model is somewhat buggy and behaves differently on different
|
||||
computers. If it becomes uncontrollable during takeoff, try using
|
||||
the --altitude command (also with --uBody set to a high number) to
|
||||
start already in flight. Increase the throttle and use small
|
||||
elevator and aileron deflections to level the aircraft.
|
||||
|
||||
Learjet24:
|
||||
Learjet 24, business jet
|
||||
flies very well
|
||||
|
||||
Marchetti:
|
||||
SIAI-Marchetti S-211 military jet trainer
|
||||
flies very smoothly, probably the easiest aircraft to fly
|
||||
|
||||
Pioneer:
|
||||
IAI Pioneer UAV, small reconnaissance unmanned aerial vehicle
|
||||
version uses stability derivatives only
|
||||
slight roll instability, but very responsive
|
||||
|
||||
Pioneer-TD:
|
||||
IAI Pioneer UAV, small reconnaissance unmanned aerial vehicle
|
||||
version uses lookup tables for lift and drag and most control
|
||||
surface deflections
|
||||
slight roll instability, but very responsive
|
||||
|
||||
T37:
|
||||
Cessna T-37 twin jet engine military trainer
|
||||
flies very well
|
||||
|
||||
TwinOtter:
|
||||
DeHavilland Canada DHC-6 Twin otter, small commuter aircraft
|
||||
NASA Glenn Twin Otter for icing research
|
||||
clean version (no ice), flies well
|
||||
|
||||
TwinOtterAllIce:
|
||||
DeHavilland Canada DHC-6 Twin otter, small commuter aircraft
|
||||
NASA Glenn Twin Otter for icing research
|
||||
note the degradation in performance after ice accretion begins
|
||||
(icing begins 2 minutes into flight; transition from clean to iced
|
||||
aerodynamics lasts 5 seconds--this is not very realistic, but you
|
||||
can vary these times and the icing severity factor, eta [0=no ice,
|
||||
1=max ice], to see the impact on performance)
|
||||
|
||||
TwinOtterTailIce:
|
||||
DeHavilland Canada DHC-6 Twin otter, small commuter aircraft
|
||||
NASA Glenn Twin Otter for icing research, tail icing only
|
||||
|
||||
TwinOtterWingIce:
|
||||
DeHavilland Canada DHC-6 Twin otter, small commuter aircraft
|
||||
NASA Glenn Twin Otter for icing research, wing icing only
|
||||
|
||||
X15:
|
||||
North American X-15, rocket-powered high-speed research aircraft
|
||||
go easy on the throttle since this is a very over-powered aircraft,
|
||||
very slow elevator but extremely responsive ailerons
|
||||
*This model is somewhat buggy and behaves differently on different
|
||||
computers. If it becomes uncontrollable during takeoff, try using
|
||||
the --altitude command (also with --uBody set to a high number) to
|
||||
start already in flight. Increase the throttle and use small
|
||||
elevator and aileron deflections to level the aircraft.
|
||||
|
||||
</pre>
|
||||
|
||||
</body>
|
||||
</html>
|
||||
63
Aircraft-uiuc/T37/aircraft.dat
Normal file
63
Aircraft-uiuc/T37/aircraft.dat
Normal file
|
|
@ -0,0 +1,63 @@
|
|||
# Jeff Scott
|
||||
# Cessna A-37/T-37, cruise configuration
|
||||
# small twin jet engine military trainer, data from:
|
||||
# Roskam, Jan. Airplane Flight Dynamics and Automatic Flight
|
||||
# Controls, Part I. Lawrence KS: DARcorporation, 1995,
|
||||
# pg 501-503
|
||||
# 03-23-2000 file creation
|
||||
|
||||
init Dz_cg 2.5 # [ft]
|
||||
|
||||
geometry bw 33.8 # [ft]
|
||||
geometry cbar 5.47 # [ft]
|
||||
geometry Sw 182.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 6360 # [lb]
|
||||
mass I_xx 7985 # [slug-ft^2]
|
||||
mass I_yy 3326 # [slug-ft^2]
|
||||
mass I_zz 11183 # [slug-ft^2]
|
||||
mass I_xz 0 # [slug-ft^2]
|
||||
|
||||
|
||||
# Roskam: CTx=0.158 (SL conditions) --> 850 lb
|
||||
# aircraft specs: 2 engines of 2850 lb static thrust each
|
||||
engine simpleSingle 2850 # [lb]
|
||||
|
||||
|
||||
CL CLo 0.2 # []
|
||||
CL CL_a 5.15 # [/rad]
|
||||
CL CL_adot 2.0 # [/rad]
|
||||
CL CL_q 4.1 # [/rad]
|
||||
CL CL_de 0.5 # [/rad]
|
||||
|
||||
CD CDo 0.048 # []
|
||||
CD CD_a 0.384 # [/rad]
|
||||
CD CD_de 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.025 # []
|
||||
Cm Cm_a -0.7 # [/rad]
|
||||
Cm Cm_adot -6.95 # [/rad]
|
||||
Cm Cm_q -14.9 # [/rad]
|
||||
Cm Cm_de -1.12 # [/rad]
|
||||
|
||||
CY CY_beta -0.346 # [/rad]
|
||||
CY CY_p -0.0827 # [/rad]
|
||||
CY CY_r 0.3 # [/rad]
|
||||
CY CY_da 0.0 # [/rad] sign reversed
|
||||
CY CY_dr 0.2 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.0944 # [/rad]
|
||||
Cl Cl_p -0.442 # [/rad]
|
||||
Cl Cl_r 0.0926 # [/rad]
|
||||
Cl Cl_da -0.181 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.015 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.1106 # [/rad]
|
||||
Cn Cn_p -0.0243 # [/rad]
|
||||
Cn Cn_r -0.139 # [/rad]
|
||||
Cn Cn_da 0.0254 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.0365 # [/rad]
|
||||
87
Aircraft-uiuc/TwinOtter/aircraft.dat
Normal file
87
Aircraft-uiuc/TwinOtter/aircraft.dat
Normal file
|
|
@ -0,0 +1,87 @@
|
|||
# Jeff Scott
|
||||
# DHC-6 Twin Otter
|
||||
# small twin turboprop engine commuter aircraft
|
||||
# This model was developed by Devesh Pokhariyal of the Smart Icing
|
||||
# Systems Aerodynamics group (Prof. Michael Bragg, head) at the
|
||||
# University of Illinois. The aircraft data is from:
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter input file (version5_bat), 5/23/00.
|
||||
# 05-23-2000 file creation
|
||||
|
||||
geometry bw 65.0 # [ft]
|
||||
geometry cbar 6.5 # [ft]
|
||||
geometry Sw 420.0 # [ft^2]
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
#controlSurface set_Long_trim_deg -3.0
|
||||
#controlSurface elevator_input Aircraft-uiuc/TwinOtter/deft.dat 1 0 700
|
||||
|
||||
mass Weight 10141 # [lb]
|
||||
mass I_xx 16039.3 # [slug-ft^2]
|
||||
mass I_yy 22841.6 # [slug-ft^2]
|
||||
mass I_zz 35807.4 # [slug-ft^2]
|
||||
mass I_xz 1102.8 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 2 engines of 462 kW each
|
||||
# ~2000 lb static thrust each
|
||||
engine simpleSingle 2000 # [lb]
|
||||
|
||||
|
||||
CL CZo -0.360 # []
|
||||
CL CZ_a -5.660 # [/rad]
|
||||
#CL CZ_a2 0.0 # [/rad]
|
||||
#CL CZ_a3 0.0 # [/rad]
|
||||
CL CZ_q -19.97 # [/rad]
|
||||
CL CZ_de -0.608 # [/rad]
|
||||
#CL CZ_deb2 0.0 # [/rad]
|
||||
#CL CZ_df 0.0 # [/rad]
|
||||
#CL CZ_adf 0.0 # [/rad]
|
||||
|
||||
CD CXo -0.0488 # []
|
||||
CD CX_a 0.223 # [/rad]
|
||||
CD CX_a2 1.659 # [/rad]
|
||||
#CD CX_a3 0.0 # [/rad]
|
||||
#CD CX_q 0.0 # [/rad]
|
||||
#CD CX_de 0.0 # [/rad]
|
||||
#CD CX_dr 0.0 # [/rad]
|
||||
#CD CX_df 0.0 # [/rad]
|
||||
#CD CX_adf 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.040 # []
|
||||
Cm Cm_a -1.310 # [/rad]
|
||||
#Cm Cm_a2 0.0 # [/rad]
|
||||
Cm Cm_q -34.2 # [/rad]
|
||||
Cm Cm_de -1.740 # [/rad]
|
||||
#Cm Cm_b2 0.0 # [/rad]
|
||||
#Cm Cm_r 0.0 # [/rad]
|
||||
#Cm Cm_df 0.0 # [/rad]
|
||||
|
||||
#CY CYo 0.0 # []
|
||||
CY CY_beta -0.6 # [/rad]
|
||||
CY CY_p -0.2 # [/rad]
|
||||
CY CY_r 0.4 # [/rad]
|
||||
#CY CY_da 0.0 # [/rad]
|
||||
CY CY_dr 0.15 # [/rad]
|
||||
#CY CY_dra 0.0 # [/rad]
|
||||
#CY CY_bdot 0.0 # [/rad]
|
||||
|
||||
#Cl Clo 0.0 # []
|
||||
Cl Cl_beta -0.08 # [/rad]
|
||||
Cl Cl_p -0.5 # [/rad]
|
||||
Cl Cl_r 0.06 # [/rad]
|
||||
Cl Cl_da -0.15 # [/rad]
|
||||
Cl Cl_dr 0.015 # [/rad]
|
||||
#Cl Cl_daa 0.0 # [/rad]
|
||||
|
||||
#Cn Cno 0.0 # [/rad]
|
||||
Cn Cn_beta 0.1 # [/rad]
|
||||
Cn Cn_p -0.06 # [/rad]
|
||||
Cn Cn_r -0.18 # [/rad]
|
||||
Cn Cn_da -0.001 # [/rad]
|
||||
Cn Cn_dr -0.125 # [/rad]
|
||||
#Cn Cn_q 0.0 # [/rad]
|
||||
#Cn Cn_b3 0.0 # [/rad]
|
||||
491
Aircraft-uiuc/TwinOtter/deft.dat
Normal file
491
Aircraft-uiuc/TwinOtter/deft.dat
Normal file
|
|
@ -0,0 +1,491 @@
|
|||
#time elevator
|
||||
0 0
|
||||
0 0
|
||||
0.0006 0
|
||||
0.001 0
|
||||
0.001 0
|
||||
0.001 0
|
||||
0.0013 0
|
||||
0.0016 0
|
||||
0.0021 0
|
||||
0.0032 0
|
||||
0.0055 0
|
||||
0.0099 0
|
||||
0.0189 0
|
||||
0.0368 -0.0011
|
||||
0.0644 -0.0009
|
||||
0.0946 -0.0047
|
||||
0.1279 -0.0052
|
||||
0.1601 -0.0017
|
||||
0.191 -0.0015
|
||||
0.2231 0.0053
|
||||
0.2531 0.0138
|
||||
0.2864 0.0262
|
||||
0.3197 0.0321
|
||||
0.3437 0.0349
|
||||
0.3677 0.0326
|
||||
0.3941 0.0271
|
||||
0.4222 0.0241
|
||||
0.4556 0.0193
|
||||
0.4889 0.0147
|
||||
0.5222 0.0084
|
||||
0.5503 0.0112
|
||||
0.5764 0.0191
|
||||
0.6026 0.0262
|
||||
0.6254 0.0332
|
||||
0.6554 0.0379
|
||||
0.6888 0.0338
|
||||
0.721 0.0288
|
||||
0.7543 0.0202
|
||||
0.7876 0.0161
|
||||
0.821 0.0161
|
||||
0.8543 0.0184
|
||||
0.8876 0.025
|
||||
0.9209 0.0325
|
||||
0.9543 0.0387
|
||||
0.9816 0.0402
|
||||
1 0.0387
|
||||
1 0.0387
|
||||
1 0.0387
|
||||
1.0124 0.0366
|
||||
1.0248 0.0346
|
||||
1.0495 0.0337
|
||||
1.0791 0.0306
|
||||
1.1114 0.0285
|
||||
1.1448 0.0258
|
||||
1.1757 0.0283
|
||||
1.2091 0.0322
|
||||
1.2424 0.041
|
||||
1.274 0.0473
|
||||
1.3073 0.0515
|
||||
1.3406 0.0564
|
||||
1.374 0.0525
|
||||
1.4073 0.0467
|
||||
1.437 0.0407
|
||||
1.4703 0.0369
|
||||
1.5028 0.0375
|
||||
1.5321 0.0393
|
||||
1.5566 0.0413
|
||||
1.5819 0.0418
|
||||
1.6085 0.0392
|
||||
1.6377 0.0354
|
||||
1.671 0.0288
|
||||
1.6989 0.0227
|
||||
1.7315 0.0209
|
||||
1.7649 0.0209
|
||||
1.7941 0.0258
|
||||
1.8262 0.0274
|
||||
1.8595 0.0258
|
||||
1.8928 0.0241
|
||||
1.9237 0.0213
|
||||
1.9502 0.021
|
||||
1.9793 0.0255
|
||||
2 0.0274
|
||||
2 0.0274
|
||||
2 0.0274
|
||||
2.0136 0.0301
|
||||
2.0273 0.0333
|
||||
2.0545 0.0361
|
||||
2.0879 0.0367
|
||||
2.1201 0.0354
|
||||
2.1498 0.029
|
||||
2.1832 0.0177
|
||||
2.2165 0.007
|
||||
2.2498 0.0016
|
||||
2.2829 0.0032
|
||||
2.3118 0.0037
|
||||
2.3402 0.0129
|
||||
2.3667 0.0214
|
||||
2.3933 0.0247
|
||||
2.4196 0.0273
|
||||
2.4522 0.0266
|
||||
2.4818 0.0219
|
||||
2.5151 0.0169
|
||||
2.5485 0.0104
|
||||
2.5785 0.0115
|
||||
2.6088 0.0173
|
||||
2.633 0.0241
|
||||
2.6573 0.0322
|
||||
2.6787 0.0382
|
||||
2.712 0.0522
|
||||
2.7453 0.0587
|
||||
2.7786 0.0596
|
||||
2.812 0.0509
|
||||
2.8453 0.0393
|
||||
2.8774 0.0326
|
||||
2.9107 0.0325
|
||||
2.9401 0.0403
|
||||
2.9734 0.0484
|
||||
3.0002 0.0612
|
||||
3.0279 0.0653
|
||||
3.0612 0.063
|
||||
3.0886 0.0584
|
||||
3.1219 0.0426
|
||||
3.1527 0.0297
|
||||
3.1819 0.0187
|
||||
3.2084 0.0085
|
||||
3.24 0.0032
|
||||
3.2734 0.0021
|
||||
3.3067 0.0016
|
||||
3.3196 0.0031
|
||||
3.3325 0.0065
|
||||
3.3473 0.0039
|
||||
3.3673 0.0044
|
||||
3.3912 0.0032
|
||||
3.4245 0.0032
|
||||
3.4579 0.0087
|
||||
3.4894 0.0332
|
||||
3.5227 0.0979
|
||||
3.5559 0.174
|
||||
3.5773 0.1884
|
||||
3.5987 0.1383
|
||||
3.6152 0.0311
|
||||
3.6266 -0.0827
|
||||
3.638 -0.2344
|
||||
3.6482 -0.3955
|
||||
3.6583 -0.5849
|
||||
3.6722 -0.8857
|
||||
3.688 -1.2767
|
||||
3.7072 -1.79
|
||||
3.7305 -2.4417
|
||||
3.7609 -3.2313
|
||||
3.7866 -3.7775
|
||||
3.8074 -4.1196
|
||||
3.8256 -4.3384
|
||||
3.841 -4.4691
|
||||
3.8534 -4.5317
|
||||
3.8662 -4.5721
|
||||
3.8827 -4.5846
|
||||
3.9041 -4.5512
|
||||
3.9375 -4.4382
|
||||
3.9708 -4.3129
|
||||
4.0041 -4.2171
|
||||
4.0359 -4.166
|
||||
4.0683 -4.1532
|
||||
4.1005 -4.163
|
||||
4.1258 -4.1722
|
||||
4.1511 -4.1719
|
||||
4.1788 -4.1573
|
||||
4.2062 -4.1239
|
||||
4.2343 -4.075
|
||||
4.2656 -4.0111
|
||||
4.2989 -3.9462
|
||||
4.3323 -3.8927
|
||||
4.3606 -3.8596
|
||||
4.392 -3.8311
|
||||
4.4254 -3.806
|
||||
4.4586 -3.7851
|
||||
4.4889 -3.7693
|
||||
4.5157 -3.7635
|
||||
4.5364 -3.7508
|
||||
4.5571 -3.7192
|
||||
4.5776 -3.6297
|
||||
4.5964 -3.4636
|
||||
4.6078 -3.3125
|
||||
4.6192 -3.1128
|
||||
4.6326 -2.803
|
||||
4.6437 -2.4949
|
||||
4.6542 -2.1585
|
||||
4.6652 -1.7653
|
||||
4.6779 -1.2648
|
||||
4.6959 -0.499
|
||||
4.7166 0.405
|
||||
4.7388 1.3243
|
||||
4.7593 2.0473
|
||||
4.7773 2.5493
|
||||
4.7925 2.8654
|
||||
4.8063 3.0589
|
||||
4.8197 3.1717
|
||||
4.8333 3.2069
|
||||
4.8446 3.1887
|
||||
4.8563 3.1272
|
||||
4.8675 3.0397
|
||||
4.8787 2.9216
|
||||
4.8926 2.7577
|
||||
4.9096 2.5405
|
||||
4.9429 2.1417
|
||||
4.9626 1.9645
|
||||
4.9771 1.8716
|
||||
4.9915 1.8143
|
||||
5.0042 1.7903
|
||||
5.017 1.7999
|
||||
5.0356 1.8528
|
||||
5.0601 1.9567
|
||||
5.0903 2.0994
|
||||
5.112 2.1896
|
||||
5.1336 2.2603
|
||||
5.1669 2.3253
|
||||
5.1939 2.3383
|
||||
5.2273 2.3255
|
||||
5.2606 2.2991
|
||||
5.2939 2.2746
|
||||
5.3273 2.263
|
||||
5.3606 2.2594
|
||||
5.3939 2.26
|
||||
5.4272 2.2582
|
||||
5.4606 2.2595
|
||||
5.4925 2.2614
|
||||
5.5258 2.2623
|
||||
5.5592 2.2596
|
||||
5.591 2.2507
|
||||
5.6244 2.2326
|
||||
5.6522 2.2151
|
||||
5.6827 2.2014
|
||||
5.7143 2.1949
|
||||
5.7446 2.1941
|
||||
5.7779 2.1949
|
||||
5.8112 2.1928
|
||||
5.841 2.1932
|
||||
5.8686 2.1887
|
||||
5.902 2.1798
|
||||
5.9353 2.1682
|
||||
5.9686 2.1597
|
||||
6.002 2.1499
|
||||
6.0311 2.1602
|
||||
6.0553 2.1857
|
||||
6.0796 2.2341
|
||||
6.1129 2.3257
|
||||
6.1403 2.3667
|
||||
6.1508 2.3518
|
||||
6.1612 2.3158
|
||||
6.1705 2.2576
|
||||
6.1797 2.1726
|
||||
6.1977 1.9126
|
||||
6.2158 1.5282
|
||||
6.2304 1.1298
|
||||
6.2428 0.7244
|
||||
6.254 0.3235
|
||||
6.2655 -0.1195
|
||||
6.2806 -0.7266
|
||||
6.2992 -1.4872
|
||||
6.321 -2.3393
|
||||
6.3359 -2.8622
|
||||
6.3507 -3.3307
|
||||
6.3629 -3.6579
|
||||
6.3736 -3.9054
|
||||
6.3846 -4.1228
|
||||
6.3961 -4.3025
|
||||
6.407 -4.4337
|
||||
6.4179 -4.5275
|
||||
6.4309 -4.5954
|
||||
6.4419 -4.6196
|
||||
6.4549 -4.6147
|
||||
6.4684 -4.5813
|
||||
6.4904 -4.4777
|
||||
6.5169 -4.3134
|
||||
6.5459 -4.1446
|
||||
6.5725 -4.0261
|
||||
6.5962 -3.9654
|
||||
6.619 -3.9504
|
||||
6.6443 -3.9736
|
||||
6.6769 -4.0413
|
||||
6.7102 -4.1265
|
||||
6.7435 -4.202
|
||||
6.7707 -4.246
|
||||
6.7955 -4.2745
|
||||
6.8289 -4.2899
|
||||
6.8604 -4.295
|
||||
6.8937 -4.2889
|
||||
6.927 -4.2688
|
||||
6.9571 -4.2411
|
||||
6.9815 -4.2095
|
||||
7.0045 -4.1814
|
||||
7.0275 -4.1538
|
||||
7.0495 -4.1264
|
||||
7.0762 -4.0949
|
||||
7.1095 -4.0526
|
||||
7.1428 -4.0104
|
||||
7.175 -3.9503
|
||||
7.197 -3.8586
|
||||
7.219 -3.6748
|
||||
7.2386 -3.3871
|
||||
7.2555 -3.0236
|
||||
7.2692 -2.6437
|
||||
7.2834 -2.1555
|
||||
7.2948 -1.7068
|
||||
7.3068 -1.1916
|
||||
7.3256 -0.3038
|
||||
7.3439 0.6002
|
||||
7.3653 1.6223
|
||||
7.3788 2.2297
|
||||
7.3923 2.7619
|
||||
7.4078 3.2783
|
||||
7.4192 3.5938
|
||||
7.4307 3.8375
|
||||
7.44 3.9892
|
||||
7.4566 4.149
|
||||
7.4704 4.1944
|
||||
7.4822 4.1669
|
||||
7.4935 4.0956
|
||||
7.5047 3.9926
|
||||
7.5177 3.841
|
||||
7.544 3.4644
|
||||
7.5724 3.0485
|
||||
7.5959 2.7663
|
||||
7.618 2.5772
|
||||
7.6384 2.4774
|
||||
7.6577 2.4504
|
||||
7.6784 2.4797
|
||||
7.701 2.5603
|
||||
7.7245 2.6722
|
||||
7.7465 2.7804
|
||||
7.7686 2.8705
|
||||
7.8019 2.9561
|
||||
7.8352 2.9776
|
||||
7.8674 2.9537
|
||||
7.895 2.917
|
||||
7.9283 2.8812
|
||||
7.9614 2.8614
|
||||
7.9947 2.86
|
||||
8.0233 2.8675
|
||||
8.0515 2.8761
|
||||
8.0806 2.8793
|
||||
8.1139 2.8755
|
||||
8.1473 2.8738
|
||||
8.177 2.8724
|
||||
8.2103 2.8714
|
||||
8.2417 2.8726
|
||||
8.2714 2.8699
|
||||
8.2998 2.8744
|
||||
8.3299 2.8921
|
||||
8.3632 2.9041
|
||||
8.388 2.8682
|
||||
8.4043 2.7996
|
||||
8.4206 2.6764
|
||||
8.4351 2.5128
|
||||
8.449 2.3081
|
||||
8.4658 1.9953
|
||||
8.4814 1.6524
|
||||
8.4944 1.3368
|
||||
8.5083 0.9808
|
||||
8.5416 0.1367
|
||||
8.5686 -0.4439
|
||||
8.5864 -0.7312
|
||||
8.6041 -0.9362
|
||||
8.6187 -1.0453
|
||||
8.6404 -1.1027
|
||||
8.6572 -1.0704
|
||||
8.6741 -0.988
|
||||
8.6895 -0.8807
|
||||
8.716 -0.6496
|
||||
8.7422 -0.4128
|
||||
8.7684 -0.2036
|
||||
8.8009 -0.0242
|
||||
8.8315 0.055
|
||||
8.862 0.0664
|
||||
8.8954 0.0314
|
||||
8.9287 -0.0144
|
||||
8.962 -0.0448
|
||||
8.9922 -0.0564
|
||||
9.0196 -0.0452
|
||||
9.0451 -0.0281
|
||||
9.0764 -0.0072
|
||||
9.1097 0.0095
|
||||
9.1431 0.0193
|
||||
9.1702 0.0241
|
||||
9.2034 0.0241
|
||||
9.2367 0.0236
|
||||
9.2673 0.0225
|
||||
9.3006 0.0192
|
||||
9.334 0.0165
|
||||
9.3624 0.0109
|
||||
9.3897 0.0081
|
||||
9.4227 0.0044
|
||||
9.454 0
|
||||
9.4869 -0.0005
|
||||
9.5202 0
|
||||
9.5533 0.0048
|
||||
9.5866 0.0128
|
||||
9.6199 0.024
|
||||
9.6533 0.0333
|
||||
9.684 0.0441
|
||||
9.7173 0.0499
|
||||
9.7506 0.0578
|
||||
9.779 0.0579
|
||||
9.8115 0.0579
|
||||
9.842 0.0544
|
||||
9.8715 0.0531
|
||||
9.9 0.0499
|
||||
9.9333 0.0493
|
||||
9.9629 0.0515
|
||||
9.9883 0.0529
|
||||
10.0216 0.0534
|
||||
10.0545 0.0564
|
||||
10.0878 0.0592
|
||||
10.1212 0.0551
|
||||
10.1492 0.058
|
||||
10.1812 0.0543
|
||||
10.2068 0.0499
|
||||
10.2401 0.0435
|
||||
10.2734 0.0402
|
||||
10.3067 0.0435
|
||||
10.3401 0.0467
|
||||
10.3711 0.0483
|
||||
10.4045 0.0499
|
||||
10.4378 0.0442
|
||||
10.4711 0.0354
|
||||
10.5044 0.0259
|
||||
10.533 0.0193
|
||||
10.5579 0.0193
|
||||
10.5912 0.0193
|
||||
10.6242 0.0193
|
||||
10.6576 0.0193
|
||||
10.6909 0.0176
|
||||
10.7233 0.0139
|
||||
10.7566 0.0139
|
||||
10.79 0.0161
|
||||
10.8233 0.0214
|
||||
10.8566 0.0295
|
||||
10.8899 0.029
|
||||
10.9233 0.0258
|
||||
10.9516 0.0209
|
||||
10.9849 0.0153
|
||||
11.0183 0.0115
|
||||
11.0516 0.0083
|
||||
11.082 0.0094
|
||||
11.1153 0.0064
|
||||
11.1486 0.0018
|
||||
11.182 0.0006
|
||||
11.2126 0.0045
|
||||
11.2386 0.011
|
||||
11.2719 0.0221
|
||||
11.3017 0.0376
|
||||
11.3351 0.0499
|
||||
11.363 0.0547
|
||||
11.3916 0.0528
|
||||
11.4187 0.0443
|
||||
11.4464 0.0323
|
||||
11.4798 0.0194
|
||||
11.5131 0.0102
|
||||
11.5441 0.0135
|
||||
11.5774 0.0233
|
||||
11.6108 0.0355
|
||||
11.6441 0.0425
|
||||
11.6774 0.0451
|
||||
11.7107 0.0466
|
||||
11.7392 0.048
|
||||
11.7711 0.0514
|
||||
11.7993 0.0515
|
||||
11.824 0.0506
|
||||
11.8486 0.0451
|
||||
11.882 0.0367
|
||||
11.9138 0.029
|
||||
11.9471 0.0278
|
||||
11.9805 0.029
|
||||
12.0138 0.036
|
||||
12.0471 0.0414
|
||||
12.0804 0.0499
|
||||
12.1137 0.0579
|
||||
12.1417 0.0571
|
||||
12.1669 0.0557
|
||||
12.192 0.0524
|
||||
12.2164 0.043
|
||||
12.2461 0.0334
|
||||
12.2794 0.0195
|
||||
12.3128 0.0092
|
||||
12.3436 0.0112
|
||||
12.3755 0.0155
|
||||
12.4088 0.0207
|
||||
12.4421 0.0258
|
||||
12.4734 0.0241
|
||||
12.49 0.0225
|
||||
156
Aircraft-uiuc/TwinOtterAllIce/aircraft.dat
Normal file
156
Aircraft-uiuc/TwinOtterAllIce/aircraft.dat
Normal file
|
|
@ -0,0 +1,156 @@
|
|||
# Jeff Scott
|
||||
# DHC-6 Twin Otter
|
||||
# small twin turboprop engine commuter aircraft with simulated
|
||||
# icing characteristics (entire aircraft iced)
|
||||
# This model was developed by Devesh Pokhariyal of the Smart Icing
|
||||
# Systems Aerodynamics group (Prof. Michael Bragg, head) at the
|
||||
# University of Illinois. The aircraft data is from:
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter input file (version5_bat), 5/23/00.
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter icing file (icesev_bat), 5/30/00.
|
||||
# Ratvasky, T.P. and Ranaudo, R.J. "Icing Effects on Aircraft
|
||||
# Stability and Control Determined from Flight Data," 31st
|
||||
# Aerospace Sciences Meeting and Exhibit, 11-14 Jan 1993,
|
||||
# AIAA-93-0398.
|
||||
# 05-30-2000 file creation
|
||||
|
||||
geometry bw 65.0 # [ft]
|
||||
geometry cbar 6.5 # [ft]
|
||||
geometry Sw 420.0 # [ft^2]
|
||||
geometry bh 20.7 # [ft] AIAA 93-0398 Table 1
|
||||
geometry ch 4.8 # [ft] AIAA 93-0398 Table 1
|
||||
geometry Sh 97.8 # [ft^2] AIAA 93-0398 Table 1
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 10141 # [lb]
|
||||
mass I_xx 16039.3 # [slug-ft^2]
|
||||
mass I_yy 22841.6 # [slug-ft^2]
|
||||
mass I_zz 35807.4 # [slug-ft^2]
|
||||
mass I_xz 1102.8 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 2 engines of 462 kW each
|
||||
# ~2000 lb static thrust each
|
||||
engine simpleSingle 2000 # [lb]
|
||||
|
||||
|
||||
CL CZo -0.360 # []
|
||||
CL CZ_a -5.660 # [/rad]
|
||||
#CL CZ_a2 0.0 # [/rad]
|
||||
#CL CZ_a3 0.0 # [/rad]
|
||||
CL CZ_q -19.97 # [/rad]
|
||||
CL CZ_de -0.608 # [/rad]
|
||||
#CL CZ_deb2 0.0 # [/rad]
|
||||
#CL CZ_df 0.0 # [/rad]
|
||||
#CL CZ_adf 0.0 # [/rad]
|
||||
|
||||
CD CXo -0.0488 # []
|
||||
CD CX_a 0.223 # [/rad]
|
||||
CD CX_a2 1.659 # [/rad]
|
||||
#CD CX_a3 0.0 # [/rad]
|
||||
#CD CX_q 0.0 # [/rad]
|
||||
#CD CX_de 0.0 # [/rad]
|
||||
#CD CX_dr 0.0 # [/rad]
|
||||
#CD CX_df 0.0 # [/rad]
|
||||
#CD CX_adf 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.040 # []
|
||||
Cm Cm_a -1.310 # [/rad]
|
||||
#Cm Cm_a2 0.0 # [/rad]
|
||||
Cm Cm_q -34.2 # [/rad]
|
||||
Cm Cm_de -1.740 # [/rad]
|
||||
#Cm Cm_b2 0.0 # [/rad]
|
||||
#Cm Cm_r 0.0 # [/rad]
|
||||
#Cm Cm_df 0.0 # [/rad]
|
||||
|
||||
#CY CYo 0.0 # []
|
||||
CY CY_beta -0.6 # [/rad]
|
||||
CY CY_p -0.2 # [/rad]
|
||||
CY CY_r 0.4 # [/rad]
|
||||
#CY CY_da 0.0 # [/rad]
|
||||
CY CY_dr 0.15 # [/rad]
|
||||
#CY CY_dra 0.0 # [/rad]
|
||||
#CY CY_bdot 0.0 # [/rad]
|
||||
|
||||
#Cl Clo 0.0 # []
|
||||
Cl Cl_beta -0.08 # [/rad]
|
||||
Cl Cl_p -0.5 # [/rad]
|
||||
Cl Cl_r 0.06 # [/rad]
|
||||
Cl Cl_da -0.15 # [/rad]
|
||||
Cl Cl_dr 0.015 # [/rad]
|
||||
#Cl Cl_daa 0.0 # [/rad]
|
||||
|
||||
#Cn Cno 0.0 # [/rad]
|
||||
Cn Cn_beta 0.1 # [/rad]
|
||||
Cn Cn_p -0.06 # [/rad]
|
||||
Cn Cn_r -0.18 # [/rad]
|
||||
Cn Cn_da -0.001 # [/rad]
|
||||
Cn Cn_dr -0.125 # [/rad]
|
||||
#Cn Cn_q 0.0 # [/rad]
|
||||
#Cn Cn_b3 0.0 # [/rad]
|
||||
|
||||
ice iceTime 120 # [s]
|
||||
ice transientTime 30 # [s]
|
||||
ice eta_ice_final 0.3 # [] do not set higher than about 0.4!
|
||||
|
||||
ice kCXo 6.52696 # []
|
||||
ice kCX_a -0.14296 # []
|
||||
ice kCX_a2 -1.59837 # []
|
||||
#ice kCX_a3 0.0 # []
|
||||
#ice kCX_q 0.0 # []
|
||||
#ice kCX_de 0.0 # []
|
||||
#ice kCX_df 0.0 # []
|
||||
#ice kCX_dr 0.0 # []
|
||||
#ice kCX_adf 0.0 # []
|
||||
|
||||
ice kCZo 0.0 # []
|
||||
ice kCZ_a -1.48148 # []
|
||||
#ice kCZ_a2 0.0 # []
|
||||
#ice kCZ_a3 0.0 # []
|
||||
ice kCZ_q -0.20741 # []
|
||||
ice kCZ_de -1.40741 # []
|
||||
#ice kCZ_df 0.0 # []
|
||||
#ice kCZ_adf 0.0 # []
|
||||
#ice kCZ_deb2 0.0 # []
|
||||
|
||||
ice kCmo 0.0 # []
|
||||
ice kCm_a -1.46667 # []
|
||||
#ice kCm_a2 0.0 # []
|
||||
#ice kCm_b2 0.0 # []
|
||||
ice kCm_q -0.51852 # []
|
||||
#ice kCm_r 0.0 # []
|
||||
ice kCm_de -1.48148 # []
|
||||
#ice kCm_df 0.0 # []
|
||||
|
||||
#ice kCYo 0.0 # []
|
||||
ice kCY_beta -2.96296 # []
|
||||
ice kCY_p 0.0 # []
|
||||
ice kCY_r 0.0 # []
|
||||
#ice kCY_da 0.0 # []
|
||||
ice kCY_dr -1.18519 # []
|
||||
#ice kCY_dra 0.0 # []
|
||||
#ice kCY_bdot 0.0 # []
|
||||
|
||||
#ice kClo 0.0 # []
|
||||
ice kCl_beta -1.48148 # []
|
||||
ice kCl_p -1.48148 # []
|
||||
ice kCl_r 0.0 # []
|
||||
ice kCl_da -1.48148 # []
|
||||
ice kCl_dr -1.18519 # []
|
||||
#ice kCl_daa 0.0 # []
|
||||
|
||||
#ice kCno 0.0 # []
|
||||
ice kCn_beta -2.96296 # []
|
||||
#ice kCn_b3 0.0 # []
|
||||
ice kCn_p 0.0 # []
|
||||
#ice kCn_q 0.0 # []
|
||||
ice kCn_r -0.88889 # []
|
||||
ice kCn_da 0.0 # []
|
||||
ice kCn_dr -1.18519 # []
|
||||
|
||||
ice beta_probe_wing 5.0 # [ft]
|
||||
ice beta_probe_tail 3.5 # [ft]
|
||||
156
Aircraft-uiuc/TwinOtterTailIce/aircraft.dat
Normal file
156
Aircraft-uiuc/TwinOtterTailIce/aircraft.dat
Normal file
|
|
@ -0,0 +1,156 @@
|
|||
# Jeff Scott
|
||||
# DHC-6 Twin Otter
|
||||
# small twin turboprop engine commuter aircraft with simulated
|
||||
# icing characteristics (tail iced)
|
||||
# This model was developed by Devesh Pokhariyal of the Smart Icing
|
||||
# Systems Aerodynamics group (Prof. Michael Bragg, head) at the
|
||||
# University of Illinois. The aircraft data is from:
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter input file (version5_bat), 5/23/00.
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter icing file (icetailsev_bat), 5/30/00.
|
||||
# Ratvasky, T.P. and Ranaudo, R.J. "Icing Effects on Aircraft
|
||||
# Stability and Control Determined from Flight Data," 31st
|
||||
# Aerospace Sciences Meeting and Exhibit, 11-14 Jan 1993,
|
||||
# AIAA-93-0398.
|
||||
# 05-30-2000 file creation
|
||||
|
||||
geometry bw 65.0 # [ft]
|
||||
geometry cbar 6.5 # [ft]
|
||||
geometry Sw 420.0 # [ft^2]
|
||||
geometry bh 20.7 # [ft] AIAA 93-0398 Table 1
|
||||
geometry ch 4.8 # [ft] AIAA 93-0398 Table 1
|
||||
geometry Sh 97.8 # [ft^2] AIAA 93-0398 Table 1
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 10141 # [lb]
|
||||
mass I_xx 16039.3 # [slug-ft^2]
|
||||
mass I_yy 22841.6 # [slug-ft^2]
|
||||
mass I_zz 35807.4 # [slug-ft^2]
|
||||
mass I_xz 1102.8 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 2 engines of 462 kW each
|
||||
# ~2000 lb static thrust each
|
||||
engine simpleSingle 2000 # [lb]
|
||||
|
||||
|
||||
CL CZo -0.360 # []
|
||||
CL CZ_a -5.660 # [/rad]
|
||||
#CL CZ_a2 0.0 # [/rad]
|
||||
#CL CZ_a3 0.0 # [/rad]
|
||||
CL CZ_q -19.97 # [/rad]
|
||||
CL CZ_de -0.608 # [/rad]
|
||||
#CL CZ_deb2 0.0 # [/rad]
|
||||
#CL CZ_df 0.0 # [/rad]
|
||||
#CL CZ_adf 0.0 # [/rad]
|
||||
|
||||
CD CXo -0.0488 # []
|
||||
CD CX_a 0.223 # [/rad]
|
||||
CD CX_a2 1.659 # [/rad]
|
||||
#CD CX_a3 0.0 # [/rad]
|
||||
#CD CX_q 0.0 # [/rad]
|
||||
#CD CX_de 0.0 # [/rad]
|
||||
#CD CX_dr 0.0 # [/rad]
|
||||
#CD CX_df 0.0 # [/rad]
|
||||
#CD CX_adf 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.040 # []
|
||||
Cm Cm_a -1.310 # [/rad]
|
||||
#Cm Cm_a2 0.0 # [/rad]
|
||||
Cm Cm_q -34.2 # [/rad]
|
||||
Cm Cm_de -1.740 # [/rad]
|
||||
#Cm Cm_b2 0.0 # [/rad]
|
||||
#Cm Cm_r 0.0 # [/rad]
|
||||
#Cm Cm_df 0.0 # [/rad]
|
||||
|
||||
#CY CYo 0.0 # []
|
||||
CY CY_beta -0.6 # [/rad]
|
||||
CY CY_p -0.2 # [/rad]
|
||||
CY CY_r 0.4 # [/rad]
|
||||
#CY CY_da 0.0 # [/rad]
|
||||
CY CY_dr 0.15 # [/rad]
|
||||
#CY CY_dra 0.0 # [/rad]
|
||||
#CY CY_bdot 0.0 # [/rad]
|
||||
|
||||
#Cl Clo 0.0 # []
|
||||
Cl Cl_beta -0.08 # [/rad]
|
||||
Cl Cl_p -0.5 # [/rad]
|
||||
Cl Cl_r 0.06 # [/rad]
|
||||
Cl Cl_da -0.15 # [/rad]
|
||||
Cl Cl_dr 0.015 # [/rad]
|
||||
#Cl Cl_daa 0.0 # [/rad]
|
||||
|
||||
#Cn Cno 0.0 # [/rad]
|
||||
Cn Cn_beta 0.1 # [/rad]
|
||||
Cn Cn_p -0.06 # [/rad]
|
||||
Cn Cn_r -0.18 # [/rad]
|
||||
Cn Cn_da -0.001 # [/rad]
|
||||
Cn Cn_dr -0.125 # [/rad]
|
||||
#Cn Cn_q 0.0 # [/rad]
|
||||
#Cn Cn_b3 0.0 # [/rad]
|
||||
|
||||
ice iceTime 120 # [s]
|
||||
ice transientTime 30 # [s]
|
||||
ice eta_ice_final 0.3 # [] do not set higher than about 0.4!
|
||||
|
||||
ice kCXo 1.58844 # []
|
||||
ice kCX_a -0.04504 # []
|
||||
ice kCX_a2 -0.58415 # []
|
||||
#ice kCX_a3 0.0 # []
|
||||
#ice kCX_q 0.0 # []
|
||||
#ice kCX_de 0.0 # []
|
||||
#ice kCX_df 0.0 # []
|
||||
#ice kCX_dr 0.0 # []
|
||||
#ice kCX_adf 0.0 # []
|
||||
|
||||
ice kCZo 0.0 # []
|
||||
ice kCZ_a -0.36593 # []
|
||||
#ice kCZ_a2 0.0 # []
|
||||
#ice kCZ_a3 0.0 # []
|
||||
ice kCZ_q -0.20741 # []
|
||||
ice kCZ_de -1.05556 # []
|
||||
#ice kCZ_df 0.0 # []
|
||||
#ice kCZ_adf 0.0 # []
|
||||
#ice kCZ_deb2 0.0 # []
|
||||
|
||||
ice kCmo 0.0 # []
|
||||
ice kCm_a -0.53244 # []
|
||||
#ice kCm_a2 0.0 # []
|
||||
#ice kCm_b2 0.0 # []
|
||||
ice kCm_q -0.51852 # []
|
||||
#ice kCm_r 0.0 # []
|
||||
ice kCm_de -1.24756 # []
|
||||
#ice kCm_df 0.0 # []
|
||||
|
||||
#ice kCYo 0.0 # []
|
||||
ice kCY_beta -2.96296 # []
|
||||
ice kCY_p 0.0 # []
|
||||
ice kCY_r 0.0 # []
|
||||
#ice kCY_da 0.0 # []
|
||||
ice kCY_dr -1.18519 # []
|
||||
#ice kCY_dra 0.0 # []
|
||||
#ice kCY_bdot 0.0 # []
|
||||
|
||||
#ice kClo 0.0 # []
|
||||
ice kCl_beta -1.48148 # []
|
||||
ice kCl_p -1.48148 # []
|
||||
ice kCl_r 0.0 # []
|
||||
ice kCl_da -1.48148 # []
|
||||
ice kCl_dr -1.18519 # []
|
||||
#ice kCl_daa 0.0 # []
|
||||
|
||||
#ice kCno 0.0 # []
|
||||
ice kCn_beta -2.96296 # []
|
||||
#ice kCn_b3 0.0 # []
|
||||
ice kCn_p 0.0 # []
|
||||
#ice kCn_q 0.0 # []
|
||||
ice kCn_r -0.88889 # []
|
||||
ice kCn_da 0.0 # []
|
||||
ice kCn_dr -1.18519 # []
|
||||
|
||||
ice beta_probe_wing 5.0 # [ft]
|
||||
ice beta_probe_tail 3.5 # [ft]
|
||||
156
Aircraft-uiuc/TwinOtterWingIce/aircraft.dat
Normal file
156
Aircraft-uiuc/TwinOtterWingIce/aircraft.dat
Normal file
|
|
@ -0,0 +1,156 @@
|
|||
# Jeff Scott
|
||||
# DHC-6 Twin Otter
|
||||
# small twin turboprop engine commuter aircraft with simulated
|
||||
# icing characteristics (wing iced)
|
||||
# This model was developed by Devesh Pokhariyal of the Smart Icing
|
||||
# Systems Aerodynamics group (Prof. Michael Bragg, head) at the
|
||||
# University of Illinois. The aircraft data is from:
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter input file (version5_bat), 5/23/00.
|
||||
# Pokhariyal, Devesh and Merret, Jason. FDC flight simulator
|
||||
# Twin Otter icing file (icewingsev_bat), 5/30/00.
|
||||
# Ratvasky, T.P. and Ranaudo, R.J. "Icing Effects on Aircraft
|
||||
# Stability and Control Determined from Flight Data," 31st
|
||||
# Aerospace Sciences Meeting and Exhibit, 11-14 Jan 1993,
|
||||
# AIAA-93-0398.
|
||||
# 05-30-2000 file creation
|
||||
|
||||
geometry bw 65.0 # [ft]
|
||||
geometry cbar 6.5 # [ft]
|
||||
geometry Sw 420.0 # [ft^2]
|
||||
geometry bh 20.7 # [ft] AIAA 93-0398 Table 1
|
||||
geometry ch 4.8 # [ft] AIAA 93-0398 Table 1
|
||||
geometry Sh 97.8 # [ft^2] AIAA 93-0398 Table 1
|
||||
|
||||
controlSurface de 20 20 # [deg] guess for now
|
||||
controlSurface da 20 20 # [deg] guess for now
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 10141 # [lb]
|
||||
mass I_xx 16039.3 # [slug-ft^2]
|
||||
mass I_yy 22841.6 # [slug-ft^2]
|
||||
mass I_zz 35807.4 # [slug-ft^2]
|
||||
mass I_xz 1102.8 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 2 engines of 462 kW each
|
||||
# ~2000 lb static thrust each
|
||||
engine simpleSingle 2000 # [lb]
|
||||
|
||||
|
||||
CL CZo -0.360 # []
|
||||
CL CZ_a -5.660 # [/rad]
|
||||
#CL CZ_a2 0.0 # [/rad]
|
||||
#CL CZ_a3 0.0 # [/rad]
|
||||
CL CZ_q -19.97 # [/rad]
|
||||
CL CZ_de -0.608 # [/rad]
|
||||
#CL CZ_deb2 0.0 # [/rad]
|
||||
#CL CZ_df 0.0 # [/rad]
|
||||
#CL CZ_adf 0.0 # [/rad]
|
||||
|
||||
CD CXo -0.0488 # []
|
||||
CD CX_a 0.223 # [/rad]
|
||||
CD CX_a2 1.659 # [/rad]
|
||||
#CD CX_a3 0.0 # [/rad]
|
||||
#CD CX_q 0.0 # [/rad]
|
||||
#CD CX_de 0.0 # [/rad]
|
||||
#CD CX_dr 0.0 # [/rad]
|
||||
#CD CX_df 0.0 # [/rad]
|
||||
#CD CX_adf 0.0 # [/rad]
|
||||
|
||||
Cm Cmo 0.040 # []
|
||||
Cm Cm_a -1.310 # [/rad]
|
||||
#Cm Cm_a2 0.0 # [/rad]
|
||||
Cm Cm_q -34.2 # [/rad]
|
||||
Cm Cm_de -1.740 # [/rad]
|
||||
#Cm Cm_b2 0.0 # [/rad]
|
||||
#Cm Cm_r 0.0 # [/rad]
|
||||
#Cm Cm_df 0.0 # [/rad]
|
||||
|
||||
#CY CYo 0.0 # []
|
||||
CY CY_beta -0.6 # [/rad]
|
||||
CY CY_p -0.2 # [/rad]
|
||||
CY CY_r 0.4 # [/rad]
|
||||
#CY CY_da 0.0 # [/rad]
|
||||
CY CY_dr 0.15 # [/rad]
|
||||
#CY CY_dra 0.0 # [/rad]
|
||||
#CY CY_bdot 0.0 # [/rad]
|
||||
|
||||
#Cl Clo 0.0 # []
|
||||
Cl Cl_beta -0.08 # [/rad]
|
||||
Cl Cl_p -0.5 # [/rad]
|
||||
Cl Cl_r 0.06 # [/rad]
|
||||
Cl Cl_da -0.15 # [/rad]
|
||||
Cl Cl_dr 0.015 # [/rad]
|
||||
#Cl Cl_daa 0.0 # [/rad]
|
||||
|
||||
#Cn Cno 0.0 # [/rad]
|
||||
Cn Cn_beta 0.1 # [/rad]
|
||||
Cn Cn_p -0.06 # [/rad]
|
||||
Cn Cn_r -0.18 # [/rad]
|
||||
Cn Cn_da -0.001 # [/rad]
|
||||
Cn Cn_dr -0.125 # [/rad]
|
||||
#Cn Cn_q 0.0 # [/rad]
|
||||
#Cn Cn_b3 0.0 # [/rad]
|
||||
|
||||
ice iceTime 120 # [s]
|
||||
ice transientTime 30 # [s]
|
||||
ice eta_ice_final 0.3 # [] do not set higher than about 0.4!
|
||||
|
||||
ice kCXo 2.64444 # []
|
||||
ice kCX_a -0.03156 # []
|
||||
ice kCX_a2 -0.13719 # []
|
||||
#ice kCX_a3 0.0 # []
|
||||
#ice kCX_q 0.0 # []
|
||||
#ice kCX_de 0.0 # []
|
||||
#ice kCX_df 0.0 # []
|
||||
#ice kCX_dr 0.0 # []
|
||||
#ice kCX_adf 0.0 # []
|
||||
|
||||
ice kCZo 0.0 # []
|
||||
ice kCZ_a -0.83259 # []
|
||||
#ice kCZ_a2 0.0 # []
|
||||
#ice kCZ_a3 0.0 # []
|
||||
ice kCZ_q -0.20741 # []
|
||||
ice kCZ_de -0.33970 # []
|
||||
#ice kCZ_df 0.0 # []
|
||||
#ice kCZ_adf 0.0 # []
|
||||
#ice kCZ_deb2 0.0 # []
|
||||
|
||||
ice kCmo 0.0 # []
|
||||
ice kCm_a -0.28346 # []
|
||||
#ice kCm_a2 0.0 # []
|
||||
#ice kCm_b2 0.0 # []
|
||||
ice kCm_q -0.51852 # []
|
||||
#ice kCm_r 0.0 # []
|
||||
ice kCm_de -0.26504 # []
|
||||
#ice kCm_df 0.0 # []
|
||||
|
||||
#ice kCYo 0.0 # []
|
||||
ice kCY_beta -2.96296 # []
|
||||
ice kCY_p 0.0 # []
|
||||
ice kCY_r 0.0 # []
|
||||
#ice kCY_da 0.0 # []
|
||||
ice kCY_dr -1.18519 # []
|
||||
#ice kCY_dra 0.0 # []
|
||||
#ice kCY_bdot 0.0 # []
|
||||
|
||||
#ice kClo 0.0 # []
|
||||
ice kCl_beta -1.48148 # []
|
||||
ice kCl_p -1.48148 # []
|
||||
ice kCl_r 0.0 # []
|
||||
ice kCl_da -1.48148 # []
|
||||
ice kCl_dr -1.18519 # []
|
||||
#ice kCl_daa 0.0 # []
|
||||
|
||||
#ice kCno 0.0 # []
|
||||
ice kCn_beta -2.96296 # []
|
||||
#ice kCn_b3 0.0 # []
|
||||
ice kCn_p 0.0 # []
|
||||
#ice kCn_q 0.0 # []
|
||||
ice kCn_r -0.88889 # []
|
||||
ice kCn_da 0.0 # []
|
||||
ice kCn_dr -1.18519 # []
|
||||
|
||||
ice beta_probe_wing 5.0 # [ft]
|
||||
ice beta_probe_tail 3.5 # [ft]
|
||||
65
Aircraft-uiuc/X15/aircraft.dat
Normal file
65
Aircraft-uiuc/X15/aircraft.dat
Normal file
|
|
@ -0,0 +1,65 @@
|
|||
# Jeff Scott
|
||||
# North American X-15
|
||||
# rocket-powered high-speed research aircraft, data from:
|
||||
# Flight Gear JSBsim X15.cfg file
|
||||
# Jon Brendt's X-15 web site
|
||||
# http://www.hal-pc.org/~jsb/X-15.html
|
||||
# 03-28-2000 file creation
|
||||
|
||||
init Dz_cg 5.0 # [ft]
|
||||
|
||||
geometry bw 22.36 # [ft]
|
||||
geometry cbar 10.27 # [ft]
|
||||
geometry Sw 200.0 # [ft^2]
|
||||
|
||||
controlSurface de 35 15 # [deg]
|
||||
controlSurface da 15 15 # [deg]
|
||||
controlSurface dr 20 20 # [deg] guess for now
|
||||
|
||||
mass Weight 31240 # [lb]
|
||||
mass I_xx 3650 # [slug-ft^2]
|
||||
mass I_yy 80000 # [slug-ft^2]
|
||||
mass I_zz 82000 # [slug-ft^2]
|
||||
mass I_xz 590 # [slug-ft^2]
|
||||
|
||||
|
||||
# aircraft specs: 51090 lb at sea level
|
||||
# 57000 lb at 45,000 ft
|
||||
# 70000 lb at peak altitude
|
||||
engine simpleSingle 51090 # [lb]
|
||||
|
||||
|
||||
#CL CLo <CLo> # []
|
||||
CL CL_a 3.5 # [/rad]
|
||||
#CL CL_adot <CL_adot> # [/rad]
|
||||
#CL CL_q <CL_q> # [/rad]
|
||||
CL CL_de 0.54 # [/rad]
|
||||
|
||||
CD CDo 0.095 # []
|
||||
#CD CDK # []
|
||||
CD CD_a 0.6 # [/rad]
|
||||
#CD CD_de <CD_de> # [/rad]
|
||||
|
||||
#Cm Cmo <Cmo> # []
|
||||
Cm Cm_a -1.2 # [/rad]
|
||||
Cm Cm_adot 0.0 # [/rad]
|
||||
Cm Cm_q -6.2 # [/rad]
|
||||
Cm Cm_de -0.9 # [/rad]
|
||||
|
||||
CY CY_beta -1.4 # [/rad]
|
||||
#CY CY_p <CY_p> # [/rad]
|
||||
#CY CY_r <CY_r> # [/rad]
|
||||
CY CY_da 0.05 # [/rad] sign reversed
|
||||
CY CY_dr 0.45 # [/rad]
|
||||
|
||||
Cl Cl_beta -0.01 # [/rad]
|
||||
Cl Cl_p -0.35 # [/rad]
|
||||
Cl Cl_r 0.04 # [/rad]
|
||||
Cl Cl_da -0.06 # [/rad] sign reversed
|
||||
Cl Cl_dr 0.012 # [/rad]
|
||||
|
||||
Cn Cn_beta 0.5 # [/rad]
|
||||
Cn Cn_p 0.0 # [/rad]
|
||||
Cn Cn_r -1.5 # [/rad]
|
||||
Cn Cn_da -0.04 # [/rad] sign reversed
|
||||
Cn Cn_dr -0.3 # [/rad]
|
||||
49
Aircraft-uiuc/models/beech99/index.html
Normal file
49
Aircraft-uiuc/models/beech99/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Beech 99 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Beech 99 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Beech 99 small
|
||||
twin-engine commuter aircraft.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2677
Aircraft-uiuc/models/beech99/linear.html
Normal file
2677
Aircraft-uiuc/models/beech99/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/beech99/refs.html
Normal file
49
Aircraft-uiuc/models/beech99/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Beech 99 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Beech 99 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 103.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 508-510.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Beech 99 Model</a> *
|
||||
<a href="refs.html">Beech 99 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/boeing747/index.html
Normal file
49
Aircraft-uiuc/models/boeing747/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Boeing 747 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Boeing 747 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Boeing 747 large
|
||||
commercial jetliner.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2720
Aircraft-uiuc/models/boeing747/linear.html
Normal file
2720
Aircraft-uiuc/models/boeing747/linear.html
Normal file
File diff suppressed because it is too large
Load diff
54
Aircraft-uiuc/models/boeing747/refs.html
Normal file
54
Aircraft-uiuc/models/boeing747/refs.html
Normal file
|
|
@ -0,0 +1,54 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Boeing 747 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Boeing 747 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 171-172.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 543-545.
|
||||
|
||||
<p>
|
||||
|
||||
Scott, Jeff. Modern Aviation Museum,
|
||||
<a href="http://fly.to/airpictures/">http://fly.to/airpictures</a>.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Boeing 747 Model</a> *
|
||||
<a href="refs.html">Boeing 747 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
53
Aircraft-uiuc/models/cessna172/index.html
Normal file
53
Aircraft-uiuc/models/cessna172/index.html
Normal file
|
|
@ -0,0 +1,53 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 172 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 172 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 10, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Cessna 172 small
|
||||
single-engine general aviation aircraft. Currently two versions of
|
||||
this model exist, a linear model using only stability derivatives
|
||||
and a nonlinear model including a lift vs. angle of attack curve to
|
||||
model stall.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="nonlinear.html">Nonlinear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2675
Aircraft-uiuc/models/cessna172/linear.html
Normal file
2675
Aircraft-uiuc/models/cessna172/linear.html
Normal file
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Load diff
2641
Aircraft-uiuc/models/cessna172/nonlinear.html
Normal file
2641
Aircraft-uiuc/models/cessna172/nonlinear.html
Normal file
File diff suppressed because it is too large
Load diff
52
Aircraft-uiuc/models/cessna172/refs.html
Normal file
52
Aircraft-uiuc/models/cessna172/refs.html
Normal file
|
|
@ -0,0 +1,52 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 172 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 172 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 10, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Peden, Tony. Flight Gear Cessna 172 model provided with Flight Gear
|
||||
0.7.1: c172_aero.c, c_172_init.c, c172_engine.c.
|
||||
|
||||
</ul>
|
||||
Note that this data is very similar to that available for the Cessna
|
||||
182 in:
|
||||
<ul>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 480-482.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Cessna 172 Model</a> *
|
||||
<a href="refs.html">Cessna 172 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/cessna310/index.html
Normal file
49
Aircraft-uiuc/models/cessna310/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 310 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 310 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated May 31, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Cessna 310 small
|
||||
twin-engine general aviation aircraft.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2677
Aircraft-uiuc/models/cessna310/linear.html
Normal file
2677
Aircraft-uiuc/models/cessna310/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/cessna310/refs.html
Normal file
49
Aircraft-uiuc/models/cessna310/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 310 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 310 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated May 31, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 249-250.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 487-489.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Cessna 310 Model</a> *
|
||||
<a href="refs.html">Cessna 310 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/cessna620/index.html
Normal file
49
Aircraft-uiuc/models/cessna620/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 620 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 620 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 1, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Cessna 620 four-engine
|
||||
general aviation aircraft.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2632
Aircraft-uiuc/models/cessna620/linear.html
Normal file
2632
Aircraft-uiuc/models/cessna620/linear.html
Normal file
File diff suppressed because it is too large
Load diff
44
Aircraft-uiuc/models/cessna620/refs.html
Normal file
44
Aircraft-uiuc/models/cessna620/refs.html
Normal file
|
|
@ -0,0 +1,44 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Cessna 620 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Cessna 620 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 1, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 515-517.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Cessna 620 Model</a> *
|
||||
<a href="refs.html">Cessna 620 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/convair880/index.html
Normal file
49
Aircraft-uiuc/models/convair880/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Convair 880 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Convair 880 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 1, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Convair 880 medium
|
||||
commercial jetliner.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2633
Aircraft-uiuc/models/convair880/linear.html
Normal file
2633
Aircraft-uiuc/models/convair880/linear.html
Normal file
File diff suppressed because it is too large
Load diff
54
Aircraft-uiuc/models/convair880/refs.html
Normal file
54
Aircraft-uiuc/models/convair880/refs.html
Normal file
|
|
@ -0,0 +1,54 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Convair 880 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Convair 880 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 1, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 274.
|
||||
|
||||
<p>
|
||||
|
||||
McCormick, Barnes W. <b>Aerodynamics, Aeronautics, and Flight
|
||||
Mechanics</b>, 2nd ed. NY: John Wiley & Sons, 1995, pg 623-624.
|
||||
|
||||
<p>
|
||||
|
||||
Nelson, Robert. <b>Flight Stability and Automatic Control</b>, 2nd
|
||||
ed., pg 414-415.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Convair 880 Model</a> *
|
||||
<a href="refs.html">Convair 880 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/f104/index.html
Normal file
49
Aircraft-uiuc/models/f104/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>F-104 Starfighter Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
F-104 Starfighter Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the F-104 Starfighter
|
||||
small single jet engine supersonic fighter.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2767
Aircraft-uiuc/models/f104/linear.html
Normal file
2767
Aircraft-uiuc/models/f104/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/f104/refs.html
Normal file
49
Aircraft-uiuc/models/f104/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>F-104 Starfighter -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
F-104 Starfighter -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 529-531.
|
||||
|
||||
<p>
|
||||
|
||||
Scott, Jeff. Modern Aviation Museum,
|
||||
<a href="http://fly.to/airpictures/">http://fly.to/airpictures</a>.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">F-104 Model</a> *
|
||||
<a href="refs.html">F-104 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/f4/index.html
Normal file
49
Aircraft-uiuc/models/f4/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>F-4 Phantom Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
F-4 Phantom Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the F-4 Phantom
|
||||
twin jet engine supersonic fighter.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2722
Aircraft-uiuc/models/f4/linear.html
Normal file
2722
Aircraft-uiuc/models/f4/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/f4/refs.html
Normal file
49
Aircraft-uiuc/models/f4/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>F-4 Phantom -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
F-4 Phantom -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 536-538.
|
||||
|
||||
<p>
|
||||
|
||||
Scott, Jeff. Modern Aviation Museum,
|
||||
<a href="http://fly.to/airpictures/">http://fly.to/airpictures</a>.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">F-4 Model</a> *
|
||||
<a href="refs.html">F-4 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
BIN
Aircraft-uiuc/models/images/alpha.gif
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Aircraft-uiuc/models/images/alpha.gif
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|
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|
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|
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|
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|
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BIN
Aircraft-uiuc/models/images/mdot.gif
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|
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|
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Aircraft-uiuc/models/images/phi.gif
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|
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Aircraft-uiuc/models/images/plms.gif
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|
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BIN
Aircraft-uiuc/models/images/psi.gif
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Aircraft-uiuc/models/images/psi.gif
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|
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BIN
Aircraft-uiuc/models/images/sigma.gif
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Aircraft-uiuc/models/images/sigma.gif
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|
After Width: | Height: | Size: 848 B |
BIN
Aircraft-uiuc/models/images/theta.gif
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Aircraft-uiuc/models/images/theta.gif
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|
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351
Aircraft-uiuc/models/index.html
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351
Aircraft-uiuc/models/index.html
Normal file
|
|
@ -0,0 +1,351 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Simulation Specifications</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Simulation Specifications
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 9, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
The UIUC Aero Model incorporated into Flight Gear utilizes
|
||||
several sets of aircraft-related data to realisticly model
|
||||
the aircraft behavior. Listed below are the models currently
|
||||
available in the UIUC Aircraft model.
|
||||
|
||||
<p>
|
||||
|
||||
<center>
|
||||
<table border="0">
|
||||
<tr>
|
||||
<th bgcolor="FFFFCC">
|
||||
<font face="arial,helvetica">
|
||||
Aircraft
|
||||
</font>
|
||||
</th>
|
||||
|
||||
<th bgcolor="FFFFCC">
|
||||
<font face="arial,helvetica">
|
||||
Description
|
||||
</font>
|
||||
</th>
|
||||
|
||||
<th bgcolor="FFFFCC">
|
||||
<font face="arial,helvetica">
|
||||
Data Type
|
||||
</font>
|
||||
</th>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="beech99/index.html">Beech 99</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
small commuter
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="boeing747/index.html">Boeing 747</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
large jetliner
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="cessna172/index.html">Cessna 172</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
general aviation
|
||||
</font>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
models stall but mostly<br>
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="cessna310/index.html">Cessna 310</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
general aviation
|
||||
</font>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="cessna620/index.html">Cessna 620</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
general aviation
|
||||
</font>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="convair880/index.html">Convair 880</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
medium jetliner
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="f104/index.html">F-104 Starfighter</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
fighter
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="f4/index.html">F-4 Phantom</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
fighter
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="learjet24/index.html">Learjet 24</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
business jet
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="marchetti/index.html">Marchetti S-211</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
jet trainer
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="pioneer/index.html">Pioneer</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
unmanned aerial vehicle
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
mostly nonlinear data with some<br>
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="t37/index.html">T-37</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
jet trainer
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/models/twinotter/index.html">Twin Otter</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
small commuter
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives<br>
|
||||
model still under development
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
<tr>
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
<a href="x15/index.html">X-15</a>
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
research aircraft
|
||||
</font>
|
||||
</td>
|
||||
|
||||
<td valign="top">
|
||||
<font face="arial,helvetica">
|
||||
linear stability derivatives
|
||||
</font>
|
||||
</td>
|
||||
</tr>
|
||||
|
||||
</table>
|
||||
</center>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/learjet24/index.html
Normal file
49
Aircraft-uiuc/models/learjet24/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Learjet 24 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Learjet 24 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Learjet 24 twin
|
||||
jet engine business jet.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2677
Aircraft-uiuc/models/learjet24/linear.html
Normal file
2677
Aircraft-uiuc/models/learjet24/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/learjet24/refs.html
Normal file
49
Aircraft-uiuc/models/learjet24/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Learjet 24 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Learjet 24 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 2, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 559-560.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 522-524.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Learjet 24 Model</a> *
|
||||
<a href="refs.html">Learjet 24 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/marchetti/index.html
Normal file
49
Aircraft-uiuc/models/marchetti/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Marchetti S-211 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Marchetti S-211 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 7, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Marchetti S-211
|
||||
single jet engine military trainer.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2676
Aircraft-uiuc/models/marchetti/linear.html
Normal file
2676
Aircraft-uiuc/models/marchetti/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/marchetti/refs.html
Normal file
49
Aircraft-uiuc/models/marchetti/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Marchetti S-211 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Marchetti S-211 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 7, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 800-801.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 494-496.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Marchetti S-211 Model</a> *
|
||||
<a href="refs.html">Marchetti S-211 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
53
Aircraft-uiuc/models/pioneer/index.html
Normal file
53
Aircraft-uiuc/models/pioneer/index.html
Normal file
|
|
@ -0,0 +1,53 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Pioneer UAV Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Pioneer UAV Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 10, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the Pioneer unmanned
|
||||
aerial vehicle. Currently two versions of this model exist, a
|
||||
linear model using only stability derivatives and a nonlinear model
|
||||
including 2D and 3D matrices of tabulated data for most aerodynamic
|
||||
coefficients.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="nonlinear.html">Nonlinear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2635
Aircraft-uiuc/models/pioneer/linear.html
Normal file
2635
Aircraft-uiuc/models/pioneer/linear.html
Normal file
File diff suppressed because it is too large
Load diff
2326
Aircraft-uiuc/models/pioneer/nonlinear.html
Normal file
2326
Aircraft-uiuc/models/pioneer/nonlinear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/pioneer/refs.html
Normal file
49
Aircraft-uiuc/models/pioneer/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>Pioneer -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
Pioneer -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 10, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Bray, Robert M. <b>A Wind Tunnel Investigation of the Pioneer
|
||||
Remotely Piloted Vehicle</b>. Montery, CA: Naval Postgraduate
|
||||
School, June 1991.
|
||||
|
||||
<p>
|
||||
|
||||
Selig, Michael S. Pioneer aircraft notes.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">Pioneer Model</a> *
|
||||
<a href="refs.html">Pioneer References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/t37/index.html
Normal file
49
Aircraft-uiuc/models/t37/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>T-37A Tweet Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
T-37A Tweet Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 7, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the T-37A Tweet
|
||||
twin jet engine military trainer.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Go to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2677
Aircraft-uiuc/models/t37/linear.html
Normal file
2677
Aircraft-uiuc/models/t37/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/t37/refs.html
Normal file
49
Aircraft-uiuc/models/t37/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>T-37A Tweet -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
T-37A Tweet -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated June 7, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 250-251.
|
||||
|
||||
<p>
|
||||
|
||||
Roskam, Jan. <b>Airplane Flight Dynamics and Automatic Flight Controls,
|
||||
Part I</b>. Lawrence KS: DARcorporation, 1995, pg 501-503.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">T-37 Model</a> *
|
||||
<a href="refs.html">T-37 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
49
Aircraft-uiuc/models/x15/index.html
Normal file
49
Aircraft-uiuc/models/x15/index.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>X-15 Simulation Model</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
X-15 Simulation Model
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
|
||||
This site provides the data needed to model the X-15 high-speed research
|
||||
aircraft.
|
||||
|
||||
<p>
|
||||
|
||||
<h2>Go to</h2>
|
||||
|
||||
<ul><h3>
|
||||
<li><a href="linear.html">Linear Model</a></li>
|
||||
<li><a href="refs.html">References</a></li>
|
||||
</h3></ul>
|
||||
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h3><b><center>
|
||||
<a href="../index.html">Back to Aircraft Models</a> *
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Back to SIS Flight Sim page</a>
|
||||
</h3></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
2721
Aircraft-uiuc/models/x15/linear.html
Normal file
2721
Aircraft-uiuc/models/x15/linear.html
Normal file
File diff suppressed because it is too large
Load diff
49
Aircraft-uiuc/models/x15/refs.html
Normal file
49
Aircraft-uiuc/models/x15/refs.html
Normal file
|
|
@ -0,0 +1,49 @@
|
|||
<html>
|
||||
<head>
|
||||
<title>X-15 -- References</title>
|
||||
</head>
|
||||
|
||||
<BODY
|
||||
bgcolor="FFFFFF" text="000000" link="0800FF"
|
||||
vlink="FF0000" alink="FF0FF8">
|
||||
|
||||
<font face="arial,helvetica">
|
||||
|
||||
<center><h1><b><i>
|
||||
X-15 -- References
|
||||
</i></b></h1></center>
|
||||
|
||||
<b><i>Graduate Research done by <a href="http://fly.to/jeffscott/">Jeff Scott</a><br>
|
||||
Advisor: <a href="http://www.uiuc.edu/ph/www/m-selig">Prof. Michael Selig</a><br>
|
||||
Applied Aerodynamics Group<br>
|
||||
Department of Aeronautical and Astronautical Engineering<br>
|
||||
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801<p>
|
||||
|
||||
Last updated April 11, 2000</i></b>
|
||||
|
||||
<p>
|
||||
<ul>
|
||||
|
||||
Berndt, Jon. JSBsim X-15 input file and X-15 website,
|
||||
<a href="http://www.hal-pc.org/~jsb/X-15.html">http://www.hal-pc.org/~jsb/X-15.html</a>.
|
||||
|
||||
<p>
|
||||
|
||||
David, Donald. <b>The Complete Encyclopedia of World Aircraft</b>.
|
||||
NY: Barnes & Noble, 1997, pg 706.
|
||||
|
||||
</ul>
|
||||
<p>
|
||||
<hr>
|
||||
<p>
|
||||
|
||||
<h5><b><center>
|
||||
<a href="http://amber.aae.uiuc.edu/~jscott/sis/">Flight Sim Home</a> *
|
||||
<a href="../index.html">Aircraft Models</a> *
|
||||
<a href="index.html">X-15 Model</a> *
|
||||
<a href="refs.html">X-15 References
|
||||
</h5></b></center>
|
||||
|
||||
</font>
|
||||
</body>
|
||||
</html>
|
||||
84
Aircraft-uiuc/runfgfs.bat
Normal file
84
Aircraft-uiuc/runfgfs.bat
Normal file
|
|
@ -0,0 +1,84 @@
|
|||
rem @ECHO OFF
|
||||
|
||||
rem Skip ahead to CONT1 if FG_ROOT has a value
|
||||
IF NOT %FG_ROOT%.==. GOTO CONT1
|
||||
|
||||
SET FG_ROOT=.
|
||||
|
||||
:CONT1
|
||||
|
||||
rem Check for the existance of the executable
|
||||
IF NOT EXIST %FG_ROOT%\BIN\FGFS.EXE GOTO ERROR1
|
||||
|
||||
rem Now that FG_ROOT has been set, run the program
|
||||
ECHO FG_ROOT = %FG_ROOT%
|
||||
|
||||
|
||||
rem Cessna 172
|
||||
%FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Cessna172 --time-offset=-0:00:00
|
||||
|
||||
rem Cessna 172 (with lift curve) from Flight Gear 0.7.1
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Cessna172-71 --time-offset=-8:00:00
|
||||
|
||||
rem Cessna 172 (with lift curve) from Flight Gear 0.7.3
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Cessna172-73 --time-offset=-5:00:00
|
||||
|
||||
rem Cessna 310
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Cessna310 --time-offset=-0:00:00
|
||||
|
||||
rem Cessna 620
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Cessna620 --time-offset=-2:00:00
|
||||
|
||||
rem Twin Otter
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/TwinOtter --time-offset=-0:00:00
|
||||
|
||||
rem Twin Otter with ice accretion in flight
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/TwinOtterAllIce --time-offset=10:00:00 --altitude=10000 --uBody=1000
|
||||
|
||||
rem Twin Otter with tail ice accretion in flight
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/TwinOtterTailIce --time-offset=10:00:00
|
||||
|
||||
rem Twin Otter with wing ice accretion in flight
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/TwinOtterWingIce --time-offset=10:00:00
|
||||
|
||||
rem Beech 99
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Beech99 --time-offset=-0:00:00
|
||||
|
||||
rem Marchetti trainer at Aspen, CO
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Marchetti --time-offset=-0:00:00 --airport-id=25U --heading=10 --disable-clouds
|
||||
|
||||
rem T-37 trainer
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/T37 --time-offset=-0:00:00
|
||||
|
||||
rem F-104 at Aspen, CO
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/F104 --time-offset=-0:00:00 --airport-id=25U --heading=10 --disable-clouds
|
||||
|
||||
rem F-4 ! DIFFICULT TO FLY !
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/F4 --time-offset=-0:00:00
|
||||
|
||||
rem Boeing 747
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Boeing747 --time-offset=-0:00:00
|
||||
|
||||
rem Convair 880 ! DIFFICULT TO FLY !
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Convair880 --time-offset=-0:00:00 --altitude=35000 --uBody=1000
|
||||
|
||||
rem Learjet 24
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Learjet24 --time-offset=-0:00:00
|
||||
|
||||
rem Pioneer at Aspen, CO
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Pioneer --time-offset=-0:00:00 --airport-id=25U --heading=270 --disable-clouds
|
||||
|
||||
rem Pioneer at Aspen, CO
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/Pioneer-TD --time-offset=-0:00:00 --airport-id=25U --heading=270 --disable-clouds
|
||||
|
||||
rem X-15 at Aspen, CO ! DIFFICULT TO FLY !
|
||||
rem %FG_ROOT%\BIN\FGFS.EXE --aircraft-dir=Aircraft-uiuc/X15 --time-offset=-0:00:00 --airport-id=25U --disable-clouds
|
||||
|
||||
|
||||
GOTO END
|
||||
|
||||
:ERROR1
|
||||
ECHO Cannot find %FG_ROOT%\BIN\FGFS.EXE
|
||||
GOTO END
|
||||
|
||||
:END
|
||||
BIN
Airports/apt_simple.gz
Normal file
BIN
Airports/apt_simple.gz
Normal file
Binary file not shown.
BIN
Airports/default.apt.gz
Normal file
BIN
Airports/default.apt.gz
Normal file
Binary file not shown.
BIN
Airports/runways.mk4
Normal file
BIN
Airports/runways.mk4
Normal file
Binary file not shown.
BIN
Airports/simple.gdbm
Normal file
BIN
Airports/simple.gdbm
Normal file
Binary file not shown.
BIN
Airports/simple.mk4
Normal file
BIN
Airports/simple.mk4
Normal file
Binary file not shown.
BIN
Astro/planets.gz
Normal file
BIN
Astro/planets.gz
Normal file
Binary file not shown.
3172
Astro/stars
Normal file
3172
Astro/stars
Normal file
File diff suppressed because it is too large
Load diff
340
COPYING
Normal file
340
COPYING
Normal file
|
|
@ -0,0 +1,340 @@
|
|||
GNU GENERAL PUBLIC LICENSE
|
||||
Version 2, June 1991
|
||||
|
||||
Copyright (C) 1989, 1991 Free Software Foundation, Inc.
|
||||
59 Temple Place, Suite 330, Boston, MA 02111-1307 USA
|
||||
Everyone is permitted to copy and distribute verbatim copies
|
||||
of this license document, but changing it is not allowed.
|
||||
|
||||
Preamble
|
||||
|
||||
The licenses for most software are designed to take away your
|
||||
freedom to share and change it. By contrast, the GNU General Public
|
||||
License is intended to guarantee your freedom to share and change free
|
||||
software--to make sure the software is free for all its users. This
|
||||
General Public License applies to most of the Free Software
|
||||
Foundation's software and to any other program whose authors commit to
|
||||
using it. (Some other Free Software Foundation software is covered by
|
||||
the GNU Library General Public License instead.) You can apply it to
|
||||
your programs, too.
|
||||
|
||||
When we speak of free software, we are referring to freedom, not
|
||||
price. Our General Public Licenses are designed to make sure that you
|
||||
have the freedom to distribute copies of free software (and charge for
|
||||
this service if you wish), that you receive source code or can get it
|
||||
if you want it, that you can change the software or use pieces of it
|
||||
in new free programs; and that you know you can do these things.
|
||||
|
||||
To protect your rights, we need to make restrictions that forbid
|
||||
anyone to deny you these rights or to ask you to surrender the rights.
|
||||
These restrictions translate to certain responsibilities for you if you
|
||||
distribute copies of the software, or if you modify it.
|
||||
|
||||
For example, if you distribute copies of such a program, whether
|
||||
gratis or for a fee, you must give the recipients all the rights that
|
||||
you have. You must make sure that they, too, receive or can get the
|
||||
source code. And you must show them these terms so they know their
|
||||
rights.
|
||||
|
||||
We protect your rights with two steps: (1) copyright the software, and
|
||||
(2) offer you this license which gives you legal permission to copy,
|
||||
distribute and/or modify the software.
|
||||
|
||||
Also, for each author's protection and ours, we want to make certain
|
||||
that everyone understands that there is no warranty for this free
|
||||
software. If the software is modified by someone else and passed on, we
|
||||
want its recipients to know that what they have is not the original, so
|
||||
that any problems introduced by others will not reflect on the original
|
||||
authors' reputations.
|
||||
|
||||
Finally, any free program is threatened constantly by software
|
||||
patents. We wish to avoid the danger that redistributors of a free
|
||||
program will individually obtain patent licenses, in effect making the
|
||||
program proprietary. To prevent this, we have made it clear that any
|
||||
patent must be licensed for everyone's free use or not licensed at all.
|
||||
|
||||
The precise terms and conditions for copying, distribution and
|
||||
modification follow.
|
||||
|
||||
GNU GENERAL PUBLIC LICENSE
|
||||
TERMS AND CONDITIONS FOR COPYING, DISTRIBUTION AND MODIFICATION
|
||||
|
||||
0. This License applies to any program or other work which contains
|
||||
a notice placed by the copyright holder saying it may be distributed
|
||||
under the terms of this General Public License. The "Program", below,
|
||||
refers to any such program or work, and a "work based on the Program"
|
||||
means either the Program or any derivative work under copyright law:
|
||||
that is to say, a work containing the Program or a portion of it,
|
||||
either verbatim or with modifications and/or translated into another
|
||||
language. (Hereinafter, translation is included without limitation in
|
||||
the term "modification".) Each licensee is addressed as "you".
|
||||
|
||||
Activities other than copying, distribution and modification are not
|
||||
covered by this License; they are outside its scope. The act of
|
||||
running the Program is not restricted, and the output from the Program
|
||||
is covered only if its contents constitute a work based on the
|
||||
Program (independent of having been made by running the Program).
|
||||
Whether that is true depends on what the Program does.
|
||||
|
||||
1. You may copy and distribute verbatim copies of the Program's
|
||||
source code as you receive it, in any medium, provided that you
|
||||
conspicuously and appropriately publish on each copy an appropriate
|
||||
copyright notice and disclaimer of warranty; keep intact all the
|
||||
notices that refer to this License and to the absence of any warranty;
|
||||
and give any other recipients of the Program a copy of this License
|
||||
along with the Program.
|
||||
|
||||
You may charge a fee for the physical act of transferring a copy, and
|
||||
you may at your option offer warranty protection in exchange for a fee.
|
||||
|
||||
2. You may modify your copy or copies of the Program or any portion
|
||||
of it, thus forming a work based on the Program, and copy and
|
||||
distribute such modifications or work under the terms of Section 1
|
||||
above, provided that you also meet all of these conditions:
|
||||
|
||||
a) You must cause the modified files to carry prominent notices
|
||||
stating that you changed the files and the date of any change.
|
||||
|
||||
b) You must cause any work that you distribute or publish, that in
|
||||
whole or in part contains or is derived from the Program or any
|
||||
part thereof, to be licensed as a whole at no charge to all third
|
||||
parties under the terms of this License.
|
||||
|
||||
c) If the modified program normally reads commands interactively
|
||||
when run, you must cause it, when started running for such
|
||||
interactive use in the most ordinary way, to print or display an
|
||||
announcement including an appropriate copyright notice and a
|
||||
notice that there is no warranty (or else, saying that you provide
|
||||
a warranty) and that users may redistribute the program under
|
||||
these conditions, and telling the user how to view a copy of this
|
||||
License. (Exception: if the Program itself is interactive but
|
||||
does not normally print such an announcement, your work based on
|
||||
the Program is not required to print an announcement.)
|
||||
|
||||
These requirements apply to the modified work as a whole. If
|
||||
identifiable sections of that work are not derived from the Program,
|
||||
and can be reasonably considered independent and separate works in
|
||||
themselves, then this License, and its terms, do not apply to those
|
||||
sections when you distribute them as separate works. But when you
|
||||
distribute the same sections as part of a whole which is a work based
|
||||
on the Program, the distribution of the whole must be on the terms of
|
||||
this License, whose permissions for other licensees extend to the
|
||||
entire whole, and thus to each and every part regardless of who wrote it.
|
||||
|
||||
Thus, it is not the intent of this section to claim rights or contest
|
||||
your rights to work written entirely by you; rather, the intent is to
|
||||
exercise the right to control the distribution of derivative or
|
||||
collective works based on the Program.
|
||||
|
||||
In addition, mere aggregation of another work not based on the Program
|
||||
with the Program (or with a work based on the Program) on a volume of
|
||||
a storage or distribution medium does not bring the other work under
|
||||
the scope of this License.
|
||||
|
||||
3. You may copy and distribute the Program (or a work based on it,
|
||||
under Section 2) in object code or executable form under the terms of
|
||||
Sections 1 and 2 above provided that you also do one of the following:
|
||||
|
||||
a) Accompany it with the complete corresponding machine-readable
|
||||
source code, which must be distributed under the terms of Sections
|
||||
1 and 2 above on a medium customarily used for software interchange; or,
|
||||
|
||||
b) Accompany it with a written offer, valid for at least three
|
||||
years, to give any third party, for a charge no more than your
|
||||
cost of physically performing source distribution, a complete
|
||||
machine-readable copy of the corresponding source code, to be
|
||||
distributed under the terms of Sections 1 and 2 above on a medium
|
||||
customarily used for software interchange; or,
|
||||
|
||||
c) Accompany it with the information you received as to the offer
|
||||
to distribute corresponding source code. (This alternative is
|
||||
allowed only for noncommercial distribution and only if you
|
||||
received the program in object code or executable form with such
|
||||
an offer, in accord with Subsection b above.)
|
||||
|
||||
The source code for a work means the preferred form of the work for
|
||||
making modifications to it. For an executable work, complete source
|
||||
code means all the source code for all modules it contains, plus any
|
||||
associated interface definition files, plus the scripts used to
|
||||
control compilation and installation of the executable. However, as a
|
||||
special exception, the source code distributed need not include
|
||||
anything that is normally distributed (in either source or binary
|
||||
form) with the major components (compiler, kernel, and so on) of the
|
||||
operating system on which the executable runs, unless that component
|
||||
itself accompanies the executable.
|
||||
|
||||
If distribution of executable or object code is made by offering
|
||||
access to copy from a designated place, then offering equivalent
|
||||
access to copy the source code from the same place counts as
|
||||
distribution of the source code, even though third parties are not
|
||||
compelled to copy the source along with the object code.
|
||||
|
||||
4. You may not copy, modify, sublicense, or distribute the Program
|
||||
except as expressly provided under this License. Any attempt
|
||||
otherwise to copy, modify, sublicense or distribute the Program is
|
||||
void, and will automatically terminate your rights under this License.
|
||||
However, parties who have received copies, or rights, from you under
|
||||
this License will not have their licenses terminated so long as such
|
||||
parties remain in full compliance.
|
||||
|
||||
5. You are not required to accept this License, since you have not
|
||||
signed it. However, nothing else grants you permission to modify or
|
||||
distribute the Program or its derivative works. These actions are
|
||||
prohibited by law if you do not accept this License. Therefore, by
|
||||
modifying or distributing the Program (or any work based on the
|
||||
Program), you indicate your acceptance of this License to do so, and
|
||||
all its terms and conditions for copying, distributing or modifying
|
||||
the Program or works based on it.
|
||||
|
||||
6. Each time you redistribute the Program (or any work based on the
|
||||
Program), the recipient automatically receives a license from the
|
||||
original licensor to copy, distribute or modify the Program subject to
|
||||
these terms and conditions. You may not impose any further
|
||||
restrictions on the recipients' exercise of the rights granted herein.
|
||||
You are not responsible for enforcing compliance by third parties to
|
||||
this License.
|
||||
|
||||
7. If, as a consequence of a court judgment or allegation of patent
|
||||
infringement or for any other reason (not limited to patent issues),
|
||||
conditions are imposed on you (whether by court order, agreement or
|
||||
otherwise) that contradict the conditions of this License, they do not
|
||||
excuse you from the conditions of this License. If you cannot
|
||||
distribute so as to satisfy simultaneously your obligations under this
|
||||
License and any other pertinent obligations, then as a consequence you
|
||||
may not distribute the Program at all. For example, if a patent
|
||||
license would not permit royalty-free redistribution of the Program by
|
||||
all those who receive copies directly or indirectly through you, then
|
||||
the only way you could satisfy both it and this License would be to
|
||||
refrain entirely from distribution of the Program.
|
||||
|
||||
If any portion of this section is held invalid or unenforceable under
|
||||
any particular circumstance, the balance of the section is intended to
|
||||
apply and the section as a whole is intended to apply in other
|
||||
circumstances.
|
||||
|
||||
It is not the purpose of this section to induce you to infringe any
|
||||
patents or other property right claims or to contest validity of any
|
||||
such claims; this section has the sole purpose of protecting the
|
||||
integrity of the free software distribution system, which is
|
||||
implemented by public license practices. Many people have made
|
||||
generous contributions to the wide range of software distributed
|
||||
through that system in reliance on consistent application of that
|
||||
system; it is up to the author/donor to decide if he or she is willing
|
||||
to distribute software through any other system and a licensee cannot
|
||||
impose that choice.
|
||||
|
||||
This section is intended to make thoroughly clear what is believed to
|
||||
be a consequence of the rest of this License.
|
||||
|
||||
8. If the distribution and/or use of the Program is restricted in
|
||||
certain countries either by patents or by copyrighted interfaces, the
|
||||
original copyright holder who places the Program under this License
|
||||
may add an explicit geographical distribution limitation excluding
|
||||
those countries, so that distribution is permitted only in or among
|
||||
countries not thus excluded. In such case, this License incorporates
|
||||
the limitation as if written in the body of this License.
|
||||
|
||||
9. The Free Software Foundation may publish revised and/or new versions
|
||||
of the General Public License from time to time. Such new versions will
|
||||
be similar in spirit to the present version, but may differ in detail to
|
||||
address new problems or concerns.
|
||||
|
||||
Each version is given a distinguishing version number. If the Program
|
||||
specifies a version number of this License which applies to it and "any
|
||||
later version", you have the option of following the terms and conditions
|
||||
either of that version or of any later version published by the Free
|
||||
Software Foundation. If the Program does not specify a version number of
|
||||
this License, you may choose any version ever published by the Free Software
|
||||
Foundation.
|
||||
|
||||
10. If you wish to incorporate parts of the Program into other free
|
||||
programs whose distribution conditions are different, write to the author
|
||||
to ask for permission. For software which is copyrighted by the Free
|
||||
Software Foundation, write to the Free Software Foundation; we sometimes
|
||||
make exceptions for this. Our decision will be guided by the two goals
|
||||
of preserving the free status of all derivatives of our free software and
|
||||
of promoting the sharing and reuse of software generally.
|
||||
|
||||
NO WARRANTY
|
||||
|
||||
11. BECAUSE THE PROGRAM IS LICENSED FREE OF CHARGE, THERE IS NO WARRANTY
|
||||
FOR THE PROGRAM, TO THE EXTENT PERMITTED BY APPLICABLE LAW. EXCEPT WHEN
|
||||
OTHERWISE STATED IN WRITING THE COPYRIGHT HOLDERS AND/OR OTHER PARTIES
|
||||
PROVIDE THE PROGRAM "AS IS" WITHOUT WARRANTY OF ANY KIND, EITHER EXPRESSED
|
||||
OR IMPLIED, INCLUDING, BUT NOT LIMITED TO, THE IMPLIED WARRANTIES OF
|
||||
MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE. THE ENTIRE RISK AS
|
||||
TO THE QUALITY AND PERFORMANCE OF THE PROGRAM IS WITH YOU. SHOULD THE
|
||||
PROGRAM PROVE DEFECTIVE, YOU ASSUME THE COST OF ALL NECESSARY SERVICING,
|
||||
REPAIR OR CORRECTION.
|
||||
|
||||
12. IN NO EVENT UNLESS REQUIRED BY APPLICABLE LAW OR AGREED TO IN WRITING
|
||||
WILL ANY COPYRIGHT HOLDER, OR ANY OTHER PARTY WHO MAY MODIFY AND/OR
|
||||
REDISTRIBUTE THE PROGRAM AS PERMITTED ABOVE, BE LIABLE TO YOU FOR DAMAGES,
|
||||
INCLUDING ANY GENERAL, SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING
|
||||
OUT OF THE USE OR INABILITY TO USE THE PROGRAM (INCLUDING BUT NOT LIMITED
|
||||
TO LOSS OF DATA OR DATA BEING RENDERED INACCURATE OR LOSSES SUSTAINED BY
|
||||
YOU OR THIRD PARTIES OR A FAILURE OF THE PROGRAM TO OPERATE WITH ANY OTHER
|
||||
PROGRAMS), EVEN IF SUCH HOLDER OR OTHER PARTY HAS BEEN ADVISED OF THE
|
||||
POSSIBILITY OF SUCH DAMAGES.
|
||||
|
||||
END OF TERMS AND CONDITIONS
|
||||
|
||||
How to Apply These Terms to Your New Programs
|
||||
|
||||
If you develop a new program, and you want it to be of the greatest
|
||||
possible use to the public, the best way to achieve this is to make it
|
||||
free software which everyone can redistribute and change under these terms.
|
||||
|
||||
To do so, attach the following notices to the program. It is safest
|
||||
to attach them to the start of each source file to most effectively
|
||||
convey the exclusion of warranty; and each file should have at least
|
||||
the "copyright" line and a pointer to where the full notice is found.
|
||||
|
||||
<one line to give the program's name and a brief idea of what it does.>
|
||||
Copyright (C) <year> <name of author>
|
||||
|
||||
This program is free software; you can redistribute it and/or modify
|
||||
it under the terms of the GNU General Public License as published by
|
||||
the Free Software Foundation; either version 2 of the License, or
|
||||
(at your option) any later version.
|
||||
|
||||
This program is distributed in the hope that it will be useful,
|
||||
but WITHOUT ANY WARRANTY; without even the implied warranty of
|
||||
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
|
||||
GNU General Public License for more details.
|
||||
|
||||
You should have received a copy of the GNU General Public License
|
||||
along with this program; if not, write to the Free Software
|
||||
Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA
|
||||
|
||||
|
||||
Also add information on how to contact you by electronic and paper mail.
|
||||
|
||||
If the program is interactive, make it output a short notice like this
|
||||
when it starts in an interactive mode:
|
||||
|
||||
Gnomovision version 69, Copyright (C) year name of author
|
||||
Gnomovision comes with ABSOLUTELY NO WARRANTY; for details type `show w'.
|
||||
This is free software, and you are welcome to redistribute it
|
||||
under certain conditions; type `show c' for details.
|
||||
|
||||
The hypothetical commands `show w' and `show c' should show the appropriate
|
||||
parts of the General Public License. Of course, the commands you use may
|
||||
be called something other than `show w' and `show c'; they could even be
|
||||
mouse-clicks or menu items--whatever suits your program.
|
||||
|
||||
You should also get your employer (if you work as a programmer) or your
|
||||
school, if any, to sign a "copyright disclaimer" for the program, if
|
||||
necessary. Here is a sample; alter the names:
|
||||
|
||||
Yoyodyne, Inc., hereby disclaims all copyright interest in the program
|
||||
`Gnomovision' (which makes passes at compilers) written by James Hacker.
|
||||
|
||||
<signature of Ty Coon>, 1 April 1989
|
||||
Ty Coon, President of Vice
|
||||
|
||||
This General Public License does not permit incorporating your program into
|
||||
proprietary programs. If your program is a subroutine library, you may
|
||||
consider it more useful to permit linking proprietary applications with the
|
||||
library. If this is what you want to do, use the GNU Library General
|
||||
Public License instead of this License.
|
||||
4
ChangeLog
Normal file
4
ChangeLog
Normal file
|
|
@ -0,0 +1,4 @@
|
|||
I haven't found a good way to maintain this file. For now you can view
|
||||
the CVS logs at:
|
||||
|
||||
http://www.menet.umn.edu/~curt/fgfs/CVSlogs/FlightGear.html
|
||||
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Add table
Reference in a new issue