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Make the plane much sloppier at high alpha and/or with the flaps
extended.  In slow flight, there's much more lateral instability now,
and adverse yaw is more obvious at the start of a turn using only
ailerons.
This commit is contained in:
david 2002-11-27 16:00:47 +00:00
parent e66946a070
commit 0b62241a7b
1 changed files with 346 additions and 213 deletions
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559
Aircraft/c172p/c172p.xml
View file

@ -1,13 +1,27 @@
<FDM_CONFIG NAME="c172" VERSION="1.60">
<!--
File: c172p.xml (originally c172.xml)
Author: Tony Peden
File: c172p.xml
Author: David Megginson (based on c172r.xml by Tony Peden)
CVS Version: $Id$
Function: Models a 1981 Cessna 172P.
Notes: Try running FlightGear using this command line,
fgfs --aircraft=c172p
Sources:
Tony Peden, c172r.xml, JSBSim (http://jsbsim.sourceforge.net/).
Jan Roskam, Airplane Flight Dynamics and Automatic Flight
Controls. Part I. DARcorporation, 1995.
Notes:
Roskam's data is for a 182, not a 172, but it should be close
enough. He gives linear coefficients for three states:
1. Climb (5.4 deg alpha).
2. Cruise (0 deg alpha).
3. Approach (4 deg alpha, and presumably, full flaps).
I have extrapolated small tables from this data to account for the
effects of flaps and alpha, especially in the lateral coefficients.
-->
<METRICS>
@ -208,89 +222,110 @@
AC_ALPHALIMITS -0.087 0.28
AC_HYSTLIMITS 0.09 0.36
<AXIS NAME="LIFT">
<GROUP NAME="CLb">
Basic_lift
<FACTOR NAME="kCLge" TYPE="VECTOR">
Change_in_lift_due_to_ground_effect
13
aero/h_b-mac-ft
none
0.0 1.203
0.1 1.127
0.15 1.090
0.2 1.073
0.3 1.046
0.4 1.055
0.5 1.019
0.6 1.013
0.7 1.008
0.8 1.006
0.9 1.003
1.0 1.002
1.1 1.0
</FACTOR>
<COEFFICIENT NAME="CLwbh" TYPE="TABLE">
Lift_due_to_alpha
17
2
aero/alpha-rad
aero/stall-hyst-norm
aero/qbar-psf | metrics/Sw-sqft
0 1
-0.09 -0.22 -0.22
0 0.25 0.25
0.09 0.73 0.73
0.1 0.83 0.78
0.12 0.92 0.79
0.14 1.02 0.81
0.16 1.08 0.82
0.17 1.13 0.83
0.19 1.19 0.85
0.21 1.25 0.86
0.24 1.35 0.88
0.26 1.44 0.9
0.28 1.47 0.92
0.3 1.43 0.95
0.32 1.38 0.99
0.34 1.3 1.05
0.36 1.15 1.15
</COEFFICIENT>
<COEFFICIENT NAME="CLDf" TYPE="VECTOR">
Delta_lift_due_to_flap_deflection
4
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft
0 0
10 0.20
20 0.30
30 0.35
</COEFFICIENT>
</GROUP>
<COEFFICIENT NAME="CLDe" TYPE="VALUE">
Lift_due_to_Elevator_Deflection
aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad
0.347
</COEFFICIENT>
<COEFFICIENT NAME="CLadot" TYPE="VALUE">
Lift_due_to_alpha_rate
aero/qbar-psf | metrics/Sw-sqft | aero/alphadot-rad_sec | aero/ci2vel
1.7
</COEFFICIENT>
<COEFFICIENT NAME="CLq" TYPE="VALUE">
Lift_due_to_pitch_rate
aero/qbar-psf | metrics/Sw-sqft | velocities/q-aero-rad_sec | aero/ci2vel
3.9
</COEFFICIENT>
</AXIS>
<AXIS NAME="DRAG">
<COEFFICIENT NAME="CDo" TYPE="VALUE">
Drag_at_zero_lift
aero/qbar-psf | metrics/Sw-sqft
0.026
<AXIS NAME="LIFT">
<GROUP NAME="CLb">
Basic_lift
<!-- Peden -->
<FACTOR NAME="kCLge" TYPE="VECTOR">
Change_in_lift_due_to_ground_effect
13
aero/h_b-mac-ft
none
0.0 1.203
0.1 1.127
0.15 1.090
0.2 1.073
0.3 1.046
0.4 1.055
0.5 1.019
0.6 1.013
0.7 1.008
0.8 1.006
0.9 1.003
1.0 1.002
1.1 1.0
</FACTOR>
<!-- Peden -->
<COEFFICIENT NAME="CLwbh" TYPE="TABLE">
Lift_due_to_alpha
17
2
aero/alpha-rad
aero/stall-hyst-norm
aero/qbar-psf | metrics/Sw-sqft
0 1
-0.09 -0.22 -0.22
0 0.25 0.25
0.09 0.73 0.73
0.1 0.83 0.78
0.12 0.92 0.79
0.14 1.02 0.81
0.16 1.08 0.82
0.17 1.13 0.83
0.19 1.19 0.85
0.21 1.25 0.86
0.24 1.35 0.88
0.26 1.44 0.9
0.28 1.47 0.92
0.3 1.43 0.95
0.32 1.38 0.99
0.34 1.3 1.05
0.36 1.15 1.15
</COEFFICIENT>
<!-- Peden -->
<COEFFICIENT NAME="CLDf" TYPE="VECTOR">
Delta_lift_due_to_flap_deflection
4
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft
0 0
10 0.20
20 0.30
30 0.35
</COEFFICIENT>
</GROUP>
<!-- Roskam p.481 -->
<COEFFICIENT NAME="CLDe" TYPE="VALUE">
Lift_due_to_Elevator_Deflection
aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad
0.43
</COEFFICIENT>
<!-- Roskam p.481 -->
<COEFFICIENT NAME="CLadot" TYPE="VALUE">
Lift_due_to_alpha_rate
aero/qbar-psf | metrics/Sw-sqft | aero/alphadot-rad_sec | aero/ci2vel
1.7
</COEFFICIENT>
<!-- Roskam p.481 -->
<COEFFICIENT NAME="CLq" TYPE="VALUE">
Lift_due_to_pitch_rate
aero/qbar-psf | metrics/Sw-sqft | velocities/q-aero-rad_sec | aero/ci2vel
3.9
</COEFFICIENT>
</AXIS>
<AXIS NAME="DRAG">
<!-- Roskam p.481 -->
<COEFFICIENT NAME="CDo" TYPE="VALUE">
Drag_at_zero_lift
aero/qbar-psf | metrics/Sw-sqft
0.0270
</COEFFICIENT>
<GROUP NAME="CDb">
Basic_drag
<!-- Peden -->
<FACTOR NAME="kCDge" TYPE="VECTOR">
Change_in_drag_due_to_ground_effect
13
@ -310,6 +345,8 @@
1.0 1.0
1.1 1.0
</FACTOR>
<!-- Peden -->
<COEFFICIENT NAME="CDDf" TYPE="VECTOR">
Delta_drag_due_to_flap_deflection
4
@ -320,6 +357,8 @@
20 0.012
30 0.018
</COEFFICIENT>
<!-- Peden -->
<COEFFICIENT NAME="CDwbh" TYPE="TABLE">
Drag_due_to_alpha
26
@ -354,173 +393,268 @@
0.314159 0.161786 0.211468 0.2388 0.253089
0.331613 0.147493 0.19508 0.221364 0.235129
0.349066 0.109678 0.151171 0.174408 0.186649
</COEFFICIENT>
</GROUP>
<COEFFICIENT NAME="CDDe" TYPE="VALUE">
Drag_due_to_Elevator_Deflection
aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
0.06
</COEFFICIENT>
<COEFFICIENT NAME="CDbeta" TYPE="VALUE">
Drag_due_to_sideslip
aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
0.17
</COEFFICIENT>
</COEFFICIENT>
</GROUP>
<!-- Roskam p.481 -->
<COEFFICIENT NAME="CDDe" TYPE="VALUE">
Drag_due_to_Elevator_Deflection
aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
0
</COEFFICIENT>
<!-- Peden -->
<COEFFICIENT NAME="CDbeta" TYPE="VALUE">
Drag_due_to_sideslip
aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
0.17
</COEFFICIENT>
</AXIS>
<AXIS NAME="SIDE">
<COEFFICIENT NAME="CYb" TYPE="VECTOR">
Side_force_due_to_beta
3
aero/beta-rad
aero/qbar-psf | metrics/Sw-sqft
-0.349 0.108
0 0
0.349 -0.108
</COEFFICIENT>
<COEFFICIENT NAME="CYda" TYPE="VALUE">
Side_force_due_to_aileron
aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
-0.05
<!-- based on Roskam p.482, clamped to +/-20deg beta -->
<COEFFICIENT NAME="CYb" TYPE="TABLE">
Side_force_due_to_beta
3
2
aero/beta-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft
0 30
-0.349 0.137 0.106
0 0 0
0.349 -0.137 -0.106
</COEFFICIENT>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="CYda" TYPE="VALUE">
Side_force_due_to_aileron
aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
0
</COEFFICIENT>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="CYdr" TYPE="VALUE">
Side_force_due_to_rudder
aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
0.098
Side_force_due_to_rudder
aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
0.187
</COEFFICIENT>
<COEFFICIENT NAME="CYp" TYPE="VALUE">
Side_force_due_to_roll_rate
aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/p-aero-rad_sec
-0.037
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="CYp" TYPE="TABLE">
Side_force_due_to_roll_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/p-aero-rad_sec
0 30
0.000 -0.075 -0.161
0.094 -0.145 -0.231
</COEFFICIENT>
<COEFFICIENT NAME="CYr" TYPE="VALUE">
Side_force_due_to_yaw_rate
aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/r-aero-rad_sec
0.21
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="CYr" TYPE="TABLE">
Side_force_due_to_yaw_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/r-aero-rad_sec
0 30
0.000 0.214 0.162
0.094 0.267 0.215
</COEFFICIENT>
</AXIS>
<AXIS NAME="ROLL">
<COEFFICIENT NAME="Clb" TYPE="VECTOR">
Roll_moment_due_to_beta
3
aero/beta-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
-0.349 0.0311
0 0
0.349 -0.0311
</COEFFICIENT>
<COEFFICIENT NAME="Clp" TYPE="VALUE">
Roll_moment_due_to_roll_rate_(roll_damping)
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
-0.47
</COEFFICIENT>
<!-- based on Roskam p.482, clamped to +/-20deg beta -->
<COEFFICIENT NAME="Clb" TYPE="VECTOR">
Roll_moment_due_to_beta
3
aero/beta-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
-0.349 0.0322
0 0
0.349 -0.0322
</COEFFICIENT>
<COEFFICIENT NAME="Clr" TYPE="VECTOR">
Roll_moment_due_to_yaw_rate
2
aero/alpha-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
0.000 0.08
0.094 0.19
</COEFFICIENT>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="Clp" TYPE="VALUE">
Roll_moment_due_to_roll_rate_(roll_damping)
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
-0.484
</COEFFICIENT>
<COEFFICIENT NAME="Clda" TYPE="VALUE">
Roll_moment_due_to_aileron
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
0.23
</COEFFICIENT>
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="Clr" TYPE="TABLE">
Roll_moment_due_to_yaw_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
0 30
0.000 0.0798 0.1246
0.094 0.1869 0.2317
</COEFFICIENT>
<COEFFICIENT NAME="Cldr" TYPE="VALUE">
Roll_moment_due_to_rudder
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
0.0147
</COEFFICIENT>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="ClDa" TYPE="VALUE">
Roll_moment_due_to_aileron
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
0.229
</COEFFICIENT>
</AXIS>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="Cldr" TYPE="VALUE">
Roll_moment_due_to_rudder
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
0.0147
</COEFFICIENT>
</AXIS>
<AXIS NAME="PITCH">
<COEFFICIENT NAME="Cmalpha" TYPE="VALUE">
Pitch_moment_due_to_alpha
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
-1.8
</COEFFICIENT>
<COEFFICIENT NAME="CmDf" TYPE="VECTOR">
Delta_pitching_moment_due_to_flap_deflection
4
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
0 0
10 -0.0654
20 -0.0981
30 -0.1140
</COEFFICIENT>
<COEFFICIENT NAME="Cmq" TYPE="VALUE">
Pitch_moment_due_to_pitch_rate
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-aero-rad_sec
-12.4
</COEFFICIENT>
<COEFFICIENT NAME="Cmadot" TYPE="VALUE">
Pitch_moment_due_to_alpha_rate
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
-5.2
</COEFFICIENT>
<COEFFICIENT NAME="Cmo" TYPE="VALUE">
<!-- Roskam p.481 -->
<COEFFICIENT NAME="Cmo" TYPE="VECTOR">
Pitching_moment_at_zero_alpha
2
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
0.1
0 0.04
30 0.09
</COEFFICIENT>
<COEFFICIENT NAME="Cmde" TYPE="VALUE">
<!-- based on Roskam p.481 -->
<COEFFICIENT NAME="Cmalpha" TYPE="TABLE">
Pitch_moment_due_to_alpha
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
0 30
0 -0.613 -0.584
0.0943 -0.650 -0.621
</COEFFICIENT>
<!-- based on Roskam p.481 -->
<COEFFICIENT NAME="Cmq" TYPE="TABLE">
Pitch_moment_due_to_pitch_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-aero-rad_sec
0 30
0 -12.4 -9.3
0.0943 -15.2 -12.1
</COEFFICIENT>
<!-- based on Roskam p.481 -->
<COEFFICIENT NAME="Cmadot" TYPE="TABLE">
Pitch_moment_due_to_alpha_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
0 30
0 -7.27 -6.66
0.0943 -5.57 -4.96
</COEFFICIENT>
<!-- based on Roskam p.481 -->
<COEFFICIENT NAME="Cmde" TYPE="TABLE">
Pitch_moment_due_to_elevator_deflection
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
-1.28
0 30
0 -1.122 -0.846
0.0943 -1.369 -1.093
</COEFFICIENT>
</AXIS>
<AXIS NAME="YAW">
<COEFFICIENT NAME="Cnb" TYPE="VECTOR">
Yaw_moment_due_to_beta
3
aero/beta-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
-0.349 -0.0227
0 0
0.349 0.0227
</COEFFICIENT>
<COEFFICIENT NAME="Cnp" TYPE="VALUE">
Yaw_moment_due_to_roll_rate
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
-0.03
</COEFFICIENT>
<!-- based on Roskam p.482, clamped to +/-20deg beta -->
<COEFFICIENT NAME="Cnb" TYPE="TABLE">
Yaw_moment_due_to_beta
3
2
aero/beta-rad
aero/alpha-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
0 0.0943
-0.349 -0.0205 -0.0317
0 0 0
0.349 0.0205 0.0317
</COEFFICIENT>
<COEFFICIENT NAME="Cnr" TYPE="VALUE">
Yaw_moment_due_to_yaw_rate
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
-0.099
</COEFFICIENT>
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="Cnp" TYPE="TABLE">
Yaw_moment_due_to_roll_rate
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
0 30
0 -0.0278 -0.0685
0.0943 -0.0649 -0.1056
</COEFFICIENT>
<COEFFICIENT NAME="Cnda" TYPE="VALUE">
Yaw_moment_due_to_aileron
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
0.0053
</COEFFICIENT>
<!-- Roskam p.482 -->
<COEFFICIENT NAME="Cnr" TYPE="VECTOR">
Yaw_moment_due_to_yaw_rate
2
aero/alpha-rad
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
0 -0.0937
0.0943 -0.1199
</COEFFICIENT>
<COEFFICIENT NAME="Cndr" TYPE="VALUE">
Yaw_moment_due_to_rudder
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
-0.043
</COEFFICIENT>
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="Cnda" TYPE="TABLE">
Yaw_moment_due_to_aileron
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
0 30
0 -0.0216 -0.0573
0.0943 -0.0504 -0.0861
</COEFFICIENT>
<!-- based on Roskam p.482 -->
<COEFFICIENT NAME="Cndr" TYPE="TABLE">
Yaw_moment_due_to_rudder
2
2
aero/alpha-rad
fcs/flap-pos-deg
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
0 30
0 -0.0645 -0.0485
0.0943 -0.0805 -0.0645
</COEFFICIENT>
</AXIS>
</AERODYNAMICS>
<!--
OUTPUT section definition
@ -582,4 +716,3 @@
PROPULSION ON
</OUTPUT>
</FDM_CONFIG>