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da40ng-jsb.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" name="DA40NG" version="2.0" release="ALPHA" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Aeromatic v 3.3.10 </author>
<filecreationdate> 06 Apr 2019 </filecreationdate>
<version>10/2021</version>
<description> Models a DA40NG. </description>
</fileheader>
<!--
Coordinate Reference Notes:
Ref. 1, p. 6 - 3: The datum plane is defined 2.194m forward the front edge
of the stub wing root rib
Comparing to ref. 1, p. 6 - 7 the root rib corresponds to x = -1.87m for
our model. This puts the datum plane at -1.87m - 2.194m = -4.064m
-->
<!--Parts are taken from the amazing GPL IDG-PA28 by Joshua Davidson (Octal450)-->
<metrics>
<wingarea unit="M2"> 13.244 </wingarea> <!-- ref. 1, p. 1 - 5 -->
<wingspan unit="M"> 11.63 </wingspan> <!-- ref. 1, p. 1 - 5 -->
<wing_incidence unit="DEG"> 1.00 </wing_incidence>
<chord unit="M"> 1.28 </chord>
<htailarea unit="M2"> 2.34 </htailarea> <!-- ref. 1, p. 1 - 6 -->
<htailarm unit="FT"> 19.69 </htailarm>
<vtailarea unit="M2"> 1.6 </vtailarea> <!-- ref. 1, p. 1 - 6 -->
<vtailarm unit="FT"> 16.40 </vtailarm>
<!-- Estimate AeroRP from in-flight CG limits:
ref. 1, p. 2-18:
most forward: 2.40m ( 940-1080kg )
2.46m ( at 1280kg )
2.469m ( at 1310kg )
most rearward: 2.53m ( 940-1310kg )
AeroRP must always be behind CG for stability reasons, assume:
AeroRP at 2.54m aft of datum plane
-->
<location name="AERORP" unit="M">
<x> -1.524 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="EYEPOINT" unit="M"> <!-- estimate from 3d model -->
<x> -1.52 </x>
<y> -0.24 </y>
<z> 0.4 </z>
</location>
<location name="VRP" unit="M"> <!-- visual model equals FDM model -->
<x> 0.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 900 </ixx>
<iyy unit="SLUG*FT2"> 1200 </iyy>
<izz unit="SLUG*FT2"> 5000 </izz> <!-- bigger value improves taxi steering, source needed for real value -->
<emptywt unit="KG"> 900 </emptywt> <!-- ref. 1, p. 6-9 (example) -->
<location name="CG" unit="M">
<!-- ref. 1, p. 6-9 (example):
Empty moment / empty mass is meter aft of datum plane
-4.064m (datum plane) + 2.422 ( meter aft of datum plane )
-->
<x> -1.642 </x>
<y> 0.00 </y>
<z> -0.2 </z>
</location>
<pointmass name="Pilot">
<weight unit="KG"> 80 </weight>
<location name="POINTMASS" unit="M">
<x> -1.764 </x> <!-- ref. 1, p. 6-7: 2.3m aft of datum plane -->
<y> -0.25 </y>
<z> 0.0 </z>
</location>
</pointmass>
<pointmass name="Copilot">
<weight unit="KG"> 80 </weight>
<location name="POINTMASS" unit="M">
<x> -1.764 </x> <!-- ref. 1, p. 6-7: 2.3m aft of datum plane -->
<y> 0.25 </y>
<z> 0.0 </z>
</location>
</pointmass>
<pointmass name="Left Passenger">
<weight unit="KG"> 0 </weight>
<location name="POINTMASS" unit="M">
<x> -0.814 </x> <!-- ref. 1, p. 6-7: 3.25m aft of datum plane -->
<y> -0.25 </y>
<z> 0.0 </z>
</location>
</pointmass>
<pointmass name="Right Passenger">
<weight unit="KG"> 0 </weight>
<location name="POINTMASS" unit="M">
<x> -0.814 </x> <!-- ref. 1, p. 6-7: 3.25m aft of datum plane -->
<y> 0.25 </y>
<z> 0.0 </z>
</location>
</pointmass>
<pointmass name="Baggage (standard compartment)">
<weight unit="KG"> 0 </weight>
<location name="POINTMASS" unit="M">
<x> -0.414 </x> <!-- ref. 1, p. 6-7: 3.65m aft of datum plane -->
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</pointmass>
</mass_balance>
<propulsion>
<engine file="AE300">
<feed> 0 </feed>
<feed> 1 </feed>
<thruster file="MTV-6-R">
<sense> 1 </sense>
<location unit="M">
<x> -3.768 </x>
<y> 0.0 </y>
<z> 0.033 </z>
</location>
<orient unit="DEG">
<pitch> 0.0 </pitch>
<roll> 0.0 </roll>
<yaw> 2.0 </yaw> <!-- 2.0 best value to stay straight on takeoff -->
</orient>
</thruster>
</engine>
<tank type="FUEL" number="0">
<location unit="M">
<x> -1.4 </x>
<y> -2.0 </y>
<z> -0.3 </z>
</location>
<capacity unit="LBS"> 100.53 </capacity>
<contents unit="LBS"> 70 </contents>
<temperature> 59 </temperature> <!-- must be degrees fahrenheit -->
</tank>
<tank type="FUEL" number="1">
<location unit="M">
<x> -1.4 </x>
<y> 2.0 </y>
<z> -0.3 </z>
</location>
<capacity unit="LBS"> 100.53 </capacity>
<contents unit="LBS"> 70 </contents>
<temperature> 59 </temperature> <!-- must be degrees fahrenheit -->
</tank>
</propulsion>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="M">
<x> -3.03444</x>
<y> -0.078441 </y>
<z> -0.99 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 4600 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 800 </damping_coeff>
<max_steer unit="DEG"> 360 </max_steer>
<brake_group> NONE </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="M">
<x> -1.25862 </x>
<y> -1.44607 </y>
<z> -0.99 </z>
</location>
<static_friction> 0.6 </static_friction>
<dynamic_friction> 0.3 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 3400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1200 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group> LEFT </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="M">
<x> -1.25862 </x>
<y> 1.44607 </y>
<z> -0.99 </z>
</location>
<static_friction> 0.6 </static_friction>
<dynamic_friction> 0.3 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 3400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1200 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group> RIGHT </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="BOGEY" name="TAIL_BUMP">
<location unit="M">
<x> 3.21935 </x>
<y> 0.0 </y>
<z> -0.145324 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1800 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group> NONE </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="M">
<x> -1.25 </x>
<y> -5.7 </y>
<z> -0.03 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT">2000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000</damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="M">
<x> -1.25 </x>
<y> 5.7 </y>
<z> -0.03 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT">2000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000</damping_coeff>
</contact>
<contact type="STRUCTURE" name="SPINNER">
<location unit="M">
<x> -4.0 </x>
<y> 0.0 </y>
<z> 0.23 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT">2000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000</damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL_TOP">
<location unit="M">
<x> 3.9 </x>
<y> 0.0 </y>
<z> 1.32 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT">2000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000</damping_coeff>
</contact>
</ground_reactions>
<system file="fuel"/> <!-- integrate advanced fuel system -->
<system file="da40-electrical.xml"/>
<system file="da40-engine.xml"/>
<system file="da40-cabin-environment.xml"/>
<flight_control file="Systems/da40-fcs.xml" />
<aerodynamics>
<!-- Aerodynamics Notes:
ref. 1, p. 1 - 5: Airfoil: Wortmann FX63-137/20 - W4
-->
<function name="aero/function/kCDge">
<description>Change in drag due to ground effect</description>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.4800
0.1000 0.5150
0.1500 0.6290
0.2000 0.7090
0.3000 0.8150
0.4000 0.8820
0.5000 0.9280
0.6000 0.9620
0.7000 0.9880
0.8000 1.0000
0.9000 1.0000
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</function>
<function name="aero/function/kCLge">
<description>Change in lift due to ground effect</description>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.2030
0.1000 1.1270
0.1500 1.0900
0.2000 1.0730
0.3000 1.0460
0.4000 1.0280
0.5000 1.0190
0.6000 1.0130
0.7000 1.0080
0.8000 1.0060
0.9000 1.0030
1.0000 1.0020
1.1000 1.0000
</tableData>
</table>
</function>
<function name="aero/alpha-wing-deg">
<description>Alpha wing (due to incidence)</description>
<sum>
<property>aero/alpha-deg</property>
<value>1</value>
</sum>
</function>
<function name="aero/function/qbar-propwash-psf">
<description>Q bar due to the propeller induced velocity </description>
<product>
<property>propulsion/engine[0]/prop-induced-velocity_fps</property>
<property>propulsion/engine[0]/prop-induced-velocity_fps</property>
<property>atmosphere/rho-slugs_ft3</property>
<value>0.5</value>
</product>
</function>
<axis name="LIFT">
<function name="aero/force/Lift_propwash">
<description>Delta lift due to propeller induced velocity</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 60.0
-0.68 0.000 0.000
0.00 0.157 0.419
0.23 0.739 1.971
0.46 0.000 0.000
</tableData>
</table>
</product>
</function>
<!--Lift/alpha for used wing profile calculated by XFLR5 (-23 to 25)-->
<function name="aero/force/Lift_alpha">
<description>Lift due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<value>0.95</value> <!--tuning factor-->
<table>
<independentVar lookup="row">aero/alpha-wing-deg</independentVar>
<tableData>
-90 0.0000
-69.9 -0.5651
-60.16 -0.7613
-50.42 -0.8791
-37.82 -1.4841
-23.000 -0.5049
-21.000 -0.4474
-17.000 -0.3305
-15.000 -0.2950
-13.000 -0.2478
-11.000 -0.2994
-9.000 -0.2808
-7.000 -0.1834
-5.000 -0.1401
-3.000 0.2506
-1.000 0.4736
1.000 0.6737
3.000 0.9000
5.000 1.1446
7.000 1.3601
9.000 1.5853
11.000 1.6112
13.000 1.5803
15.000 1.6284
17.000 1.5600
19.000 1.1705
21.000 1.1555
23.000 1.1880
25.000 1.1812
34.38 2.4865
50.42 1.1209
60.16 0.9707
69.9 0.7205
90 0.0000
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_pitch_rate">
<description>Lift due to pitch rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>velocities/q-aero-rad_sec</property>
<property>aero/ci2vel</property>
<value> 7.3499 </value>
</product>
</function>
<function name="aero/force/Lift_alpha_rate">
<description>Lift due to alpha rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alphadot-rad_sec</property>
<property>aero/ci2vel</property>
<value> 2.4053 </value>
</product>
</function>
<function name="aero/force/Lift_elevator">
<description>Lift due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value> 0.4739 </value>
<!-- From c172p (GPL):
stall and spin (6):
elevator loss of efficiency when stalled
-->
<table>
<independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
<independentVar lookup="column">aero/alpha-deg</independentVar>
<tableData>
18 25 35 45 55 65 90
-0.49 1 0.5 0.2 0.1 0.1 0.1 0.1
0 1 0.6 0.3 0.15 0.1 0.1 0.1
0.40 1 0.9 0.8 0.7 0.6 0.5 0.4
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_flap">
<description>Delta Lift due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.0123 </value>
</product>
</function>
</axis>
<axis name="DRAG">
<!--Minimum drag: Fuselage+gear-->
<function name="aero/force/Drag_minimum">
<description>Minimum drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value> 0.0 </value>
</product>
</function>
<function name="aero/force/Drag_alpha">
<description>Drag due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCDge</property>
<value>1.07</value>
<!-- Tuning factor -->
<table>
<independentVar lookup="row">aero/alpha-wing-deg</independentVar>
<tableData><!--Data from XFLR5 for wing profile (only)-->
-90 1.4097
-24 0.2794248
-23 0.2666956
-22 0.2547104
-21 0.2463513
-20 0.2421844
-17 0.1983887
-16 0.1875978
-15 0.1815053
-14 0.1719089
-13 0.1554324
-12 0.1470788
-11 0.1474383
-10 0.1355344
-9 0.1266563
-8 0.112973
-7 0.09930508
-6 0.08771448
-5 0.07806702
-4 0.03587057
-3 0.03068254
-2 0.0286035
-1 0.03148496
0 0.03160175
1 0.03315386
2 0.03242366
3 0.03293901
4 0.03256778
5 0.03269471
6 0.03179481
7 0.03307064
8 0.02941788
9 0.02980358
10 0.03234835
11 0.03763734
12 0.04717603
13 0.05635169
14 0.06388856
15 0.07348026
16 0.08459226
17 0.1058408
19 0.2576396
20 0.2658857
21 0.2855086
22 0.3093093
23 0.3206512
24 0.3416924
25 0.3660205
90 1.4097
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_induced">
<description>Induced drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<value> 0.0 </value> <!-- 1/(pi*AR*e), AR=8.53, e=0.84, value=0.044 -->
</product>
</function>
<function name="aero/force/Drag_mach">
<description>Drag due to mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.0000
0.70 0.0000
1.10 0.0230
1.80 0.0150
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_beta">
<description>Drag due to sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<tableData>
-1.57 0.800
-0.26 0.040
0.00 0.000
0.26 0.040
1.57 0.800
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_elevator">
<description>Drag due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs>
<property>fcs/elevator-pos-rad</property>
</abs>
<value> 0.0400 </value>
</product>
</function>
<function name="aero/force/Drag_flap">
<description>Drag due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.0018 </value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/force/Side_beta">
<description>Side force due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<value> -0.5615 </value>
</product>
</function>
<function name="aero/force/Side_roll_rate">
<description>Side force due to roll rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar lookup="row">aero/Re</independentVar>
<tableData>
1477348 0.8704
1625083 0.0742
2216022 0.0330
2956678 0.0185
</tableData>
</table>
</product>
</function>
<function name="aero/force/Side_yaw_rate">
<description>Side force due to yaw rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value> 0.4828 </value>
</product>
</function>
<function name="aero/force/Side_rudder">
<description>Side force due to rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.1699 </value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/moment/Pitch_propwash">
<description>Pitch moment due to propeller induced velocity</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<value>-0.1</value>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 60.0
-0.03 0.000 0.000
0.00 -0.142 -0.378
0.23 -0.667 -1.779
0.30 0.000 0.000
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_alpha">
<description>Pitch moment due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<value> -0.7 </value>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<description>Pitch moment due to elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 -2.3876
2.0 -0.5969
</tableData>
</table>
</product>
</function>
<!--The elevator trim tab also does provide a (small) amount of pitch control (inverted!)-->
<function name="aero/moment/Pitch_elevator_trim_tab">
<description>Pitch moment due to elevator trim tab</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/pitch-trim-cmd-norm</property>
<value>0.05</value>
</product>
</function>
<function name="aero/moment/Pitch_damp">
<description>Pitch moment due to pitch rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<value> -37.5372 </value>
</product>
</function>
<function name="aero/moment/Pitch_alphadot">
<description>Pitch moment due to alpha rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<value> -12.2841 </value>
</product>
</function>
</axis>
<axis name="ROLL">
<!--
<function name="aero/moment/Roll_differential_propwash">
<description>Roll moment due to differential propwash</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/alpha-rad</property>
<value> 0.4085 </value>
</product>
</function>-->
<function name="aero/moment/Roll_beta">
<description>Roll moment due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<property>fcs/gear-no-wow</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
1477348 1625083 2216022 2956678
-0.0349 -0.6715 -0.3814 -0.3663 -0.3611
0.3491 -0.6715 -0.3814 -0.3663 -0.3611
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_damp">
<description>Roll moment due to roll rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value> -2.3559 </value>
</product>
</function>
<function name="aero/moment/Roll_yaw">
<description>Roll moment due to yaw rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
1477348 1625083 2216022 2956678
-0.0349 0.0934 0.0934 0.0934 0.0934
0.3491 11.7688 1.6834 1.6834 1.6834
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_aileron">
<description>Roll moment due to aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/stall-hyst-norm</independentVar>
<tableData>
0.0 1.0
0.279 1.00 0.30
0.297 0.30 0.30
0.349 -0.15 -0.15
</tableData>
</table>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.600
2.0 0.0425
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_rudder">
<description>Roll moment due to rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.0100 </value>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/moment/Yaw_beta">
<description>Yaw moment due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value> 0.1160 </value>
</product>
</function>
<function name="aero/moment/Yaw_roll_rate">
<description>Yaw moment due to roll rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-rad_sec</property>
<table>
<independentVar lookup="row">aero/Re</independentVar>
<tableData>
1477348 -0.3742
1625083 -0.0319
2216022 -0.0142
2956678 -0.0080
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_damp">
<description>Yaw moment due to yaw rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value> -0.1794 </value>
</product>
</function>
<function name="aero/moment/Yaw_rudder">
<description>Yaw moment due to rudder</description>
<product>
<sum>
<property>aero/qbar-psf</property>
<property>aero/function/qbar-propwash-psf</property>
</sum>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value> -0.08 </value>
</product>
</function>
<function name="aero/moment/Yaw_aileron">
<description>Adverse yaw</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<value> -0.0200 </value>
</product>
</function>
<function name="aero/moment/Yaw_prop">
<description>Yaw moment due to spiraling propwash</description>
<product>
<property>aero/function/qbar-propwash-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<value>-0.018</value>
</product>
</function>
</axis>
</aerodynamics>
<external_reactions>
</external_reactions>
</fdm_config>