From ff3f4fedf5706e70906925f37a9f596690666c81 Mon Sep 17 00:00:00 2001 From: j4strngs Date: Wed, 1 May 2002 01:19:26 +0000 Subject: [PATCH] move uiuc beech99 docs --- Aircraft-uiuc/models/beech99/index.html | 49 - Aircraft-uiuc/models/beech99/linear.html | 2677 ---------------------- Aircraft-uiuc/models/beech99/refs.html | 49 - 3 files changed, 2775 deletions(-) delete mode 100644 Aircraft-uiuc/models/beech99/index.html delete mode 100644 Aircraft-uiuc/models/beech99/linear.html delete mode 100644 Aircraft-uiuc/models/beech99/refs.html diff --git a/Aircraft-uiuc/models/beech99/index.html b/Aircraft-uiuc/models/beech99/index.html deleted file mode 100644 index 732f62657..000000000 --- a/Aircraft-uiuc/models/beech99/index.html +++ /dev/null @@ -1,49 +0,0 @@ - - -Beech 99 Simulation Model - - - - - - -

-Beech 99 Simulation Model -

- -Graduate Research done by Jeff Scott
-Advisor: Prof. Michael Selig
-Applied Aerodynamics Group
-Department of Aeronautical and Astronautical Engineering
-University of Illinois at Urbana-Champaign, Urbana, Illinois 61801

- -Last updated April 11, 2000 - -

- -This site provides the data needed to model the Beech 99 small -twin-engine commuter aircraft. - -

- -

Go to

- - - -

-

-

- -

-Back to Aircraft Models * -Go to SIS Flight Sim page -

- - - - \ No newline at end of file diff --git a/Aircraft-uiuc/models/beech99/linear.html b/Aircraft-uiuc/models/beech99/linear.html deleted file mode 100644 index c01601db6..000000000 --- a/Aircraft-uiuc/models/beech99/linear.html +++ /dev/null @@ -1,2677 +0,0 @@ - - -Beech 99 -- Linear Model - - - - - - -

-Beech 99 -- Linear Model -

- -Graduate Research done by Jeff Scott
-Advisor: Prof. Michael Selig
-Applied Aerodynamics Group
-Department of Aeronautical and Astronautical Engineering
-University of Illinois at Urbana-Champaign, Urbana, Illinois 61801

- -Last updated April 11, 2000 - -

- -The linear aerodynamics model uses stability derivatives to approximate -actual aircraft behavior. The Beech 99 linear model is based on the -following flight conditions (low altitude cruise): - -

- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Flight Conditions -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - h - - - - Altitude - - - - altitude above sea level - - - - ft - - - - 5000 - - - - Roskam pg 508 - - - - - -
- - - - - - Alpha - - - - angle of attack - - - - deg - - - - 0 - - - - Roskam pg 508 - - - - - -
- - V - - - - V_true_kts - - - - velocity (true air speed) - - - - kts - - - - 201 - - - - Roskam pg 508 - - - - Mach 0.31 - -
- - q - - - - Dynamic_pressure - - - - dynamic pressure - - - - lb/ft2 - - - - 118.3 - - - - Roskam pg 508 - - - - - -
- - C.G. - - - - - - - - - center of gravity location - - - - % - - - - 16 - - - - Roskam pg 508 - - - - - -
- - CL - - - - CL - - - - lift coefficient - - - - - - - - - ? - - - - - - - - not available - -
- - CD - - - - CD - - - - drag coefficient - - - - - - - - - ? - - - - - - - - not available - -
- - Cm - - - - Cm - - - - pitching moment coefficient - - - - - - - - - ? - - - - - - - - not available - -
-
- -

- -The data input into the simulator is listed in the following tables: - -

- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Geometry -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - b - - - - bw - - - - wingspan - - - - ft - - - - 46 - - - - Roskam pg 508 - - - - - -
- - - - - - cbar - - - - wing mean aerodynamic chord - - - - ft - - - - 6.5 - - - - Roskam pg 508 - - - - - -
- - S - - - - Sw - - - - wing surface area - - - - ft2 - - - - 280 - - - - Roskam pg 508 - - - - - -
- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Control Surface Geometry -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - emax - - - - demax - - - - maximum elevator deflection - - - - deg - - - - +20 - - - - - - - - - guess - -
- - emin - - - - demin - - - - minimum elevator deflection - - - - deg - - - - -20 - - - - - - - - - guess - -
- - amax - - - - damax - - - - maximum aileron deflection - - - - deg - - - - +20 - - - - - - - - - guess - -
- - amin - - - - damin - - - - minimum aileron deflection - - - - deg - - - - -20 - - - - - - - - - guess - -
- - rmax - - - - drmax - - - - maximum rudder deflection - - - - deg - - - - +20 - - - - - - - - - guess - -
- - rmin - - - - drmin - - - - minimum rudder deflection - - - - deg - - - - -20 - - - - - - - - - guess - -
- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Mass Data -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - W - - - - Weight - - - - weight at flight condition - - - - lb - - - - 7000 - - - - Roskam pg 508 - - - - converted to Mass
[slug/ft3] in code - -
- - Ixx - - - - I_xx - - - - roll inertia - - - - slug ft2 - - - - 10085 - - - - Roskam pg 508 - - - - - -
- - Iyy - - - - I_yy - - - - pitch inertia - - - - slug ft2 - - - - 15148 - - - - Roskam pg 508 - - - - - -
- - Izz - - - - I_zz - - - - yaw inertia - - - - slug ft2 - - - - 23046 - - - - Roskam pg 508 - - - - - -
- - Ixz - - - - I_xz - - - - lateral cross inertia - - - - slug ft2 - - - - 1600 - - - - Roskam pg 508 - - - - - -
- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Propulsion Data -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - Tmax - - - - simpleSingleMaxThrust - - - - maximum thrust - - - - lb - - - - 1550 - - - - Roskam pg 509 - - - - estimated from CTx
- at sea level - -
- - Pmax - - - - - - - - - maximum power - - - - kW - - - - 1106 - - - - David pg 103 - - - - max engine rating
- not used in code - -
- -

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
-
- Aerodynamic Data -
-
- - Variable - - - - Variable
in Code - - 		- - Description - - - - Units - - - - Value(s) - - - - Source - - - - Notes - -
- - CD0 - - - - CDo - - - - drag coefficient at =0 - - - - - - - - - 0.027 - - - - Roskam pg 509 - - - - - -
- - CD - - - - CD_a - - - - drag curve slope - - - - 1/rad - - - - 0.131 - - - - Roskam pg 509 - - - - - -
- - CDe - - - - CD_de - - - - drag due to elevator - - - - 1/rad - - - - 0 - - - - Roskam pg 509 - - - - e positive down - -
- - CL0 - - - - CLo - - - - lift coefficient at =0 - - - - - - - - - 0.201 - - - - Roskam pg 509 - - - - - -
- - CL - - - - CL_a - - - - lift curve slope - - - - 1/rad - - - - 5.48 - - - - Roskam pg 509 - - - - - -
- - CL - - - - CL_adot - - - - lift due to angle of attack rate - - - - 1/rad - - - - 2.5 - - - - Roskam pg 509 - - - - - -
- - CLq - - - - CL_q - - - - lift due to pitch rate - - - - 1/rad - - - - 8.1 - - - - Roskam pg 509 - - - - - -
- - CLe - - - - CL_de - - - - lift due to elevator - - - - 1/rad - - - - 0.60 - - - - Roskam pg 509 - - - - e positive down - -
- - Cm0 - - - - Cmo - - - - pitch moment coefficient at =0 - - - - - - - - - 0.05 - - - - Roskam pg 509 - - - - - -
- - Cm - - - - Cm_a - - - - pitch moment due to angle of attack - - - - 1/rad - - - - -1.89 - - - - Roskam pg 509 - - - - - -
- - Cm - - - - Cm_adot - - - - pitch moment due to angle of attack rate - - - - 1/rad - - - - -9.1 - - - - Roskam pg 509 - - - - - -
- - Cmq - - - - Cm_q - - - - pitch moment due to pitch rate - - - - 1/rad - - - - -34.0 - - - - Roskam pg 509 - - - - - -
- - Cme - - - - Cm_de - - - - pitching moment due to elevator - - - - 1/rad - - - - -2.0 - - - - Roskam pg 509 - - - - e positive down - -
- - CY - - - - CY_beta - - - - side force fue to sideslip angle - - - - 1/rad - - - - -0.59 - - - - Roskam pg 510 - - - - - -
- - CYp - - - - CY_p - - - - side force due to roll rate - - - - 1/rad - - - - -0.19 - - - - Roskam pg 510 - - - - - -
- - CYr - - - - CY_r - - - - side force due to yaw rate - - - - 1/rad - - - - 0.39 - - - - Roskam pg 510 - - - - - -
- - CYa - - - - CY_da - - - - side force due to aileron - - - - 1/rad - - - - 0 - - - - Roskam pg 510 - - - - a positive
right aileron up - -
- - CYr - - - - CY_dr - - - - side force due to rudder - - - - 1/rad - - - - 0.148 - - - - Roskam pg 510 - - - - r positive left - -
- - Cl - - - - Cl_beta - - - - dihedral effect - - - - 1/rad - - - - -0.13 - - - - Roskam pg 510 - - - - - -
- - Clp - - - - Cl_p - - - - roll damping - - - - 1/rad - - - - -0.50 - - - - Roskam pg 510 - - - - - -
- - Clr - - - - Cl_r - - - - roll moment due to yaw rate - - - - 1/rad - - - - 0.14 - - - - Roskam pg 510 - - - - - -
- - Cla - - - - Cl_da - - - - roll moment due to aileron - - - - 1/rad - - - - -0.156 - - - - Roskam pg 510 - - - - a positive
right aileron up - -
- - Clr - - - - Cl_dr - - - - roll moment due to rudder - - - - 1/rad - - - - 0.0109 - - - - Roskam pg 510 - - - - r positive left - -
- - Cn - - - - Cn_beta - - - - weathercock stability - - - - 1/rad - - - - 0.080 - - - - Roskam pg 510 - - - - - -
- - Cnp - - - - Cn_p - - - - adverse yaw - - - - 1/rad - - - - 0.019 - - - - Roskam pg 510 - - - - - -
- - Cnr - - - - Cn_r - - - - yaw damping - - - - 1/rad - - - - -0.197 - - - - Roskam pg 510 - - - - - -
- - Cna - - - - Cn_da - - - - yaw moment due to aileron - - - - 1/rad - - - - 0.0012 - - - - Roskam pg 510 - - - - a positive
right aileron up - -
- - Cnr - - - - Cn_dr - - - - yaw moment due to rudder - - - - 1/rad - - - - -0.0772 - - - - Roskam pg 510 - - - - r positive left - -
-

- -

-

-

- -

-Flight Sim Home * -Aircraft Models * -Beech 99 Model * -Beech 99 References
-
- - - - \ No newline at end of file diff --git a/Aircraft-uiuc/models/beech99/refs.html b/Aircraft-uiuc/models/beech99/refs.html deleted file mode 100644 index 1f4e62226..000000000 --- a/Aircraft-uiuc/models/beech99/refs.html +++ /dev/null @@ -1,49 +0,0 @@ - - -Beech 99 -- References - - - - - - -

-Beech 99 -- References -

- -Graduate Research done by Jeff Scott
-Advisor: Prof. Michael Selig
-Applied Aerodynamics Group
-Department of Aeronautical and Astronautical Engineering
-University of Illinois at Urbana-Champaign, Urbana, Illinois 61801

- -Last updated April 11, 2000 - -

-

-

-

-

- -

-Flight Sim Home * -Aircraft Models * -Beech 99 Model * -Beech 99 References -
- - - - \ No newline at end of file