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KC-137R.xml
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<?xml version="1.0"?>
<!--###################################################################################
Lake of Constance Hangar :: M.Kraus
Boeing 707 for Flightgear Septemper 2013
This file is licenced under the terms of the GNU General Public Licence V2 or later
###################################################################################
-->
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="707" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author>M.Kraus :: Lake of Constance Hangar</author>
<filecreationdate>2014-02-24</filecreationdate>
<version>2.2.4</version>
<description>Boeing 707 CFM-56</description>
</fileheader>
<!--
File: 707.xml
Inputs:
name: 707
type: four-engine transonic transport
max weight: 333795.105 lb
wing span: 142.3954 ft
length: 152.92741 ft
wing area: 3046.483963 sq-ft
gear type: tricycle
retractable?: yes
# engines: 4
engine type: turbine
engine layout: wings
yaw damper: smooth yoke behaviour
Outputs:
wing loading: 109.57 lb/sq-ft
payload: 45108.5 lbs
CL-alpha: 4.4 per radian
CL-0: 0.2
CL-max: 1.2
CD-0: 0.017
K: 0.042
-->
<metrics>
<wingarea unit="FT2"> 3046.48 </wingarea>
<wingspan unit="FT" > 142.40 </wingspan>
<wing_incidence> 2.00 </wing_incidence>
<chord unit="FT" > 21.39 </chord>
<htailarea unit="FT2"> 761.62 </htailarea>
<htailarm unit="FT" > 68.82 </htailarm>
<vtailarea unit="FT2"> 609.30 </vtailarea>
<vtailarm unit="FT" > 68.82 </vtailarm>
<location name="AERORP" unit="IN">
<x> 0.00 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 0.00 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="VRP" unit="IN">
<x> 0.00</x>
<y> 0.00</y>
<z> 0.00</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 2322405 </ixx>
<iyy unit="SLUG*FT2"> 2886669 </iyy>
<izz unit="SLUG*FT2"> 5260000 </izz>
<emptywt unit="LBS" > 137526 </emptywt>
<location name="CG" unit="IN">
<x> 0.0 </x>
<y> 0.0 </y>
<z>-45.20 </z>
</location>
<pointmass name="CREW">
<weight unit="LBS">540</weight>
<location name="POINTMASS" unit="IN">
<x>-600</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="PASSENGER FIRST CLASS">
<weight unit="LBS"> 0</weight><!-- passengers-->
<location name="POINTMASS" unit="IN">
<x>-400</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="PASSENGER SECOND CLASS">
<weight unit="LBS"> 0</weight><!-- passengers-->
<location name="POINTMASS" unit="IN">
<x>-100</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="PASSENGER SECOND CLASS">
<weight unit="LBS"> 0</weight><!-- passengers-->
<location name="POINTMASS" unit="IN">
<x> 50</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="LUGGAGE 1">
<weight unit="LBS"> 0</weight><!-- cargo or more passengers -->
<location name="POINTMASS" unit="IN">
<x>-400</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="LUGGAGE 2">
<weight unit="LBS"> 0</weight><!-- cargo or more passengers -->
<location name="POINTMASS" unit="IN">
<x>-100</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
<pointmass name="LUGGAGE 3">
<weight unit="LBS"> 0</weight><!-- cargo or more passengers -->
<location name="POINTMASS" unit="IN">
<x> 50</x>
<y> 0</y>
<z> 0</z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> -618.44 </x>
<y> 0.00 </y>
<z> -114.00 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 90000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 6000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC">12000</damping_coeff_rebound>
<relaxation_velocity>
<rolling unit="FT/SEC">0.6</rolling>
<side unit="FT/SEC">0.6</side>
</relaxation_velocity>
<force_lag_filter>
<rolling> 120.0 </rolling>
<side>120.0 </side>
</force_lag_filter>
<wheel_slip_filter> 120.0 </wheel_slip_filter>
<max_steer unit="DEG"> 35 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 71.65 </x>
<y> -98.81 </y>
<z> -116.3 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.70 </dynamic_friction>
<rolling_friction> 0.04 </rolling_friction>
<spring_coeff unit="LBS/FT"> 230000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">140000.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x> 71.65 </x>
<y> 98.81 </y>
<z> -116.3 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.70 </dynamic_friction>
<rolling_friction> 0.04 </rolling_friction>
<spring_coeff unit="LBS/FT"> 230000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">140000.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE_CRASHED">
<location unit="IN">
<x> -618.44 </x>
<y> 0.00 </y>
<z> -50.00 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 360600.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x> 411.00 </x>
<y> -72.88 </y>
<z> -43.65 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 360600.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 411.00 </x>
<y> 72.88 </y>
<z> -43.65 </z>
</location>
<static_friction> 0.55 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 360600.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
</contact>
</ground_reactions>
<propulsion>
<engine file="CFM-56">
<location unit="IN">
<x> 22.11 </x>
<y>-586.50 </y>
<z> -46.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>5</feed>
<thruster file="direct">
<location unit="IN">
<x> 22.11 </x>
<y>-586.50 </y>
<z> -46.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="CFM-56">
<location unit="IN">
<x>-164.20 </x>
<y>-393.62 </y>
<z> -77.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>4</feed>
<thruster file="direct">
<location unit="IN">
<x>-164.20 </x>
<y>-393.62 </y>
<z> -77.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="CFM-56">
<location unit="IN">
<x>-164.20 </x>
<y> 393.62 </y>
<z> -77.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>2</feed>
<thruster file="direct">
<location unit="IN">
<x>-164.20 </x>
<y> 393.62 </y>
<z> -77.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="CFM-56">
<location unit="IN">
<x> 22.11 </x>
<y> 586.50 </y>
<z> -46.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>1</feed>
<thruster file="direct">
<location unit="IN">
<x> 22.11 </x>
<y> 586.50 </y>
<z> -46.00 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<!-- Reserve 4 tank right -->
<tank type="FUEL" number="0">
<location unit="IN">
<x> 39.37 </x>
<y> 700.00 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 2941.00 </capacity>
<contents unit="LBS"> 1470.00 </contents>
</tank>
<!-- Main 4 tank right -->
<tank type="FUEL" number="1">
<location unit="IN">
<x> 120.12 </x>
<y> 507.10 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 15564.00 </capacity>
<contents unit="LBS"> 7782.00 </contents>
</tank>
<!-- Main 3 tank right -->
<tank type="FUEL" number="2">
<location unit="IN">
<x> -74.10 </x>
<y> 176.30 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 27262.00 </capacity>
<contents unit="LBS"> 13631.00 </contents>
</tank>
<!-- center tank -->
<tank type="FUEL" number="3">
<location unit="IN">
<x> 0.0 </x>
<y> 0.0 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 68293.00 </capacity>
<contents unit="LBS"> 34146.00 </contents>
</tank>
<!-- Main 2 tank left -->
<tank type="FUEL" number="4">
<location unit="IN">
<x> -74.10 </x>
<y> -176.30 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 27262.00 </capacity>
<contents unit="LBS"> 13631.00 </contents>
</tank>
<!-- Main 1 tank left -->
<tank type="FUEL" number="5">
<location unit="IN">
<x> 120.12 </x>
<y> -507.10 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 15564.00 </capacity>
<contents unit="LBS"> 7782.00 </contents>
</tank>
<!-- Reserve 1 tank left -->
<tank type="FUEL" number="6">
<location unit="IN">
<x> 39.37 </x>
<y> -700.00 </y>
<z> -16.65 </z>
</location>
<capacity unit="LBS"> 2941.00 </capacity>
<contents unit="LBS"> 1470.00 </contents>
</tank>
</propulsion>
<system file="pushback"/>
<flight_control name="707-MK">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<gain>0.007</gain>
<range>
<min>-20</min>
<max>20</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator Position Normalizer">
<input>fcs/pitch-trim-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<gain>0.006</gain>
<range>
<min>-40</min>
<max>40</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron Position Normalizer">
<input>fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>fcs/roll-trim-sum</input>
<gain>0.006</gain>
<range>
<min>-40</min>
<max>40</max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Position Normalizer">
<input>fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-command-sum</input>
<gain>0.007</gain>
<range>
<min>-30</min>
<max>30</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder Position Normalizer">
<input>fcs/rudder-command-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Aeromechanical">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position> 0 </position>
<time> 0 </time>
</setting>
<setting>
<position> 2 </position>
<time> 3 </time>
</setting>
<setting>
<position> 4 </position>
<time> 3 </time>
</setting>
<setting>
<position> 6 </position>
<time> 3 </time>
</setting>
<setting>
<position> 10 </position>
<time> 3 </time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="flap normalization">
<input>fcs/flap-pos-deg</input>
<domain>
<min> 0 </min>
<max> 10 </max>
</domain>
<range>
<min> 0 </min>
<max> 1 </max>
</range>
<output>fcs/flap-pos-norm</output>
</aerosurface_scale>
<kinematic name="Gear Control">
<input>gear/gear-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>10</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
<switch name="Leading Edge Flaps">
<default value="0"/>
<test logic="AND" value="1.0000">
fcs/flap-cmd-norm GT 0.1
/controls/special/slats-switch == 1
</test>
<output>fcs/LE-flap-cmd-norm</output>
</switch>
<kinematic name="Leading Edge Flaps Control">
<input>fcs/LE-flap-cmd-norm</input>
<traverse>
<setting>
<position>0.0</position>
<time>0.0</time>
</setting>
<setting>
<position>0.5</position>
<time>2.0</time>
</setting>
<setting>
<position>1.0</position>
<time>2.0</time>
</setting>
</traverse>
<output>fcs/wing-fold-pos-norm</output>
</kinematic>
</channel>
<channel name="Speedbrake">
<kinematic name="Spoiler Control">
<input>fcs/spoiler-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>0.25</position>
<time>1.0</time>
</setting>
<setting>
<position>0.5</position>
<time>1.0</time>
</setting>
<setting>
<position>0.75</position>
<time>1.0</time>
</setting>
<setting>
<position>1</position>
<time>1.0</time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
</channel>
</flight_control>
<aerodynamics>
<axis name="LIFT"> <!-- ########################################################### -->
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-0.20 -0.780
0.00 0.170
0.23 1.400
0.50 0.740
0.60 0.340
<!--
-0.20 -0.680
0.00 0.240
0.23 1.400
0.60 0.740
-->
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLflap">
<description>Delta_Lift_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.000
2.0000 0.040
4.0000 0.150
6.0000 0.200
10.0000 0.400
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLsb">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<!--<value>-0.08</value>-->
<value>-0.2</value>
</product>
</function>
<!-- the LE flap -->
<function name="aero/coefficient/CDLEflap">
<description>Lift_due_to_leading_edge_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/wing-fold-pos-norm</property>
<value>0.2</value>
</product>
</function>
<function name="aero/coefficient/CLde">
<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>0.2</value>
</product>
</function>
<!-- only for the difference between the newer and older engines -->
<function name="aero/coefficient/JT4">
<description>Lift_due_to_stronger_Engines</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/engines/engine[0]/n1</property> <!--only with the stronger TJ4 engines-->
<property>/engines/engine[1]/n1</property> <!--only with the stronger TJ4 engines-->
<property>/engines/engine[2]/n1</property> <!--only with the stronger TJ4 engines-->
<property>/engines/engine[3]/n1</property> <!--only with the stronger TJ4 engines-->
<property>/sim/multiplay/generic/int[8]</property> <!--only with the stronger TJ4 engines-->
<value>0.000000002</value>
</product>
</function>
<function name="aero/coefficient/CLground">
<description>Lift_due_ground_reactions</description>
<product>
<table>
<independentVar>position/h-agl-ft</independentVar>
<tableData>
0 0.105
10 0.149
20 0.203
27 0
</tableData>
</table>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
</product>
</function>
<function name="aero/coefficient/StabTrim">
<description>Lift_due_to_stabilizer</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/b707/stabilizer/cutout</property> <!-- stabilization nose up down with different weights -->
<value>0.2</value>
</product>
</function>
</axis>
<axis name="DRAG"> <!-- ########################################################### -->
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-1.57 1.500
-0.26 0.022
0.00 0.017
0.26 0.022
1.57 1.500
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDi">
<description>Induced_drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
<value>0.042</value>
</product>
</function>
<function name="aero/coefficient/CDmach">
<description>Drag_due_to_mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.000
0.79 0.000
1.10 0.023
1.80 0.015
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDflap">
<description>Drag_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<!--<value> 0.018 </value>-->
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.000
2.0000 0.012
4.0000 0.014 <!-- takeoff-->
6.0000 0.024 <!-- approach-->
10.0000 0.035 <!-- landing -->
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDgear">
<description>Drag_due_to_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.011</value>
</product>
</function>
<function name="aero/coefficient/CDsb">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<!--<value>0.017</value>-->
<value>0.05</value>
</product>
</function>
<function name="aero/coefficient/CDbeta">
<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 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDde">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs>
<property>fcs/elevator-pos-norm</property>
</abs>
<value>0.04</value>
</product>
</function>
<function name="aero/coefficient/CDcrash">
<description>After_crash_drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<property>/b707/crashed</property> <!-- if airplane crashed -->
<value>10</value>
</product>
</function>
</axis>
<axis name="SIDE"> <!-- ########################################################### -->
<function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<value>-1</value>
</product>
</function>
</axis>
<axis name="ROLL"> <!-- ########################################################### -->
<function name="aero/coefficient/Clb">
<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>
<value>-0.1</value>
</product>
</function>
<function name="aero/coefficient/Clp">
<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>-0.4</value>
</product>
</function>
<function name="aero/coefficient/Clr">
<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>
<value>0.005</value>
</product>
</function>
<function name="aero/coefficient/Clda">
<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">velocities/mach</independentVar>
<tableData>
0.0 0.100
2.0 0.033
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cldr">
<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>0.008</value>
</product>
</function>
</axis>
<axis name="PITCH"> <!-- ########################################################### -->
<function name="aero/coefficient/Cmalpha">
<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/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>