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747-200.xml
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<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="747-200" version="2.0" release="PRODUCTION"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> </author>
<filecreationdate> 11 August 2019 </filecreationdate>
<version> 2.04 </version>
<description> 747-200 with JT9D-7R4G2 </description>
<license>
<licenseName>GPL (General Public License)</licenseName>
<licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
</license>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. It has been validated only to the extent that it seems
to "fly right", and possibly to comply to published, publicly known,
performance data (maximum speed, endurance, etc.). Thus, this model
is meant for educational and entertainment purposes only.
This simulation model is not endorsed by the manufacturer. This model
is not to be sold.
</note>
<note>maximum takeoff weight 833,000 lb.</note>
<note>extended range fuel 54,388 US gal (364,400 lb).</note>
<note>center of gravity between 13.0 % and 33.0 % of MAC.</note>
<note>spoilers, leading edge flaps.</note>
<note>gear height adjusted by 3D model, supposed accurate.</note>
<note>nose wheel steering is off.</note>
<note>747 coefficients.</note>
<note>pushback and wake.</note>
<limitation>at landing the arm of CG must be weak, otherwise pitch control is too slow to react at touch-down.</limitation>
<!--
File: 747-200.xml
Author: Aero-Matic v 0.71
Inputs:
name: 747-200
type: four-engine transonic transport
max weight: 833000 lb
wing span: 195.67 ft
length: 231.85 ft
wing area: 5500 sq-ft
gear type: tricycle
retractable?: yes
# engines: 4
engine type: turbine
engine layout: wings
yaw damper? yes
Outputs:
wing loading: 151.45 lb/sq-ft
CL-alpha: 4.4 per radian
CL-0: 0.2
CL-max: 1.2
CD-0: 0.017
K: 0.042
-->
<reference
refID="FAA certificate, a20we"
author="FAA"
title="http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet"
date="23 December 1970, 747-200B"/>
<documentation>
MAC : 327.8 in.
Datum :
- balance arm datum corresponds to body station 0, at 90 in. forward of nose.
- horizontal distance of datum to nose gear jack points in 384.7 in.
Leading edge of MAC : 1258 in.
MAC starts at 1168 in. from nose, and continues above the gears.
</documentation>
<reference
refID="747 airplane characteristics, D6-58236"
author="Boeing"
title="http://www.boeing.com/"
date="May 1984"/>
<documentation>
Dimensions : lateral position of engines.
gear tracks.
Gear stearing.
Tanks typical quantities.
</documentation>
<documentation>
- http://www.aoe.vt.edu/~mason/Mason_f/M96SC02.pdf/ (Willian H. Mason) :
CG range : 13.0 / 33.0 % MAC.
- http://www.bh.com/companions/034074152X/appendices/data-a/table-3/table.htm :
Horizontal tail : area 136.60 m2, arm 32.50 m, 1/4 chord sweep 32.00 m.
Vertical tail : area 77.10 m2, arm 30.00 m, 1/4 chord sweep 45.00 m.
V2 177 kt, Vapp 141 kt, Vne/Mme 445 kt / 0.95 Mach.
- http://www.airliners.net/discussions/tech_ops/read.main/52218/6/#ID52218 :
V2 190 kt (max takeoff load), climbs without flaps only at V2 + 100 kt.
VREF 154 kt (max landing load).
</documentation>
<reference
refID="Nasa CR D-2144"
author="Robert K. Heffley and Wayne F. Jewell"
title="Aircraft handling qualities data"
date="December 1972"/>
<documentation>
- http://ntrs.nasa.gov/ :
747 coefficients :
- mach 0.20 is the landing configuration (flaps 30).
- mach 0.25 is the approach configuration (flaps 20).
Estimation of drag and lift at zero lift :
- CDo = CD - ( CDalpha x alpha + CDmach x mach + CDflaps + CDLE + CDgear ).
- CLo = CL - ( CLalpha x alpha + CLmach x mach + CLflaps + CLLE + CLde x ds ).
- table IX-3 provides alpha and mach.
- stabilizer, drag and lift are guessed from drawings.
- CDde, which is not included in CDo formula, adjusts range.
</documentation>
</fileheader>
<metrics>
<documentation>
- aero reference point is at empty load CG (33 % MAC) :
less arm for landing; control is supposed easier if CG is forwards.
- VRP at nose.
- gear estimated at 25 ft (300 in.) below nose.
- wing incidence helps the takeoff.
</documentation>
<wingarea unit="FT2"> 5500 </wingarea>
<wingspan unit="FT"> 195.67 </wingspan>
<chord unit="FT"> 27.32 </chord> <!-- aeromatic 28.11 -->
<htailarea unit="FT2"> 1470.35 </htailarea> <!-- aeromatic 1375.00 -->
<htailarm unit="FT"> 106.63 </htailarm> <!-- aeromatic 104.33 -->
<vtailarea unit="FT2"> 829.9 </vtailarea> <!-- aeromatic 1100.00 -->
<vtailarm unit="FT"> 0 </vtailarm>
<!-- AC_LV 98.43 --> <!-- ft --> <!-- aeromatic 104.33 -->
<wing_incidence unit="DEG"> 2 </wing_incidence>
<location name="AERORP" unit="IN">
<x> 1276 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 218 </x>
<y> -21 </y>
<z> 80 </z>
</location>
<location name="VRP" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<documentation>
- operational empty weight = 376170 lb + 160 lb for extended fuel range.
- empty CG at 23 % MAC (no payload).
- the point mass is the equivalent payload to get 833000 lb; adjusted so that
CG at empty fuel is 33 % MAC (1276 in.), full load 20 % (1232 in.).
</documentation>
<ixx unit="SLUG*FT2"> 3.80337e+07 </ixx>
<iyy unit="SLUG*FT2"> 6.02827e+07 </iyy>
<izz unit="SLUG*FT2"> 9.79195e+07 </izz>
<ixy unit="SLUG*FT2"> 0 </ixy>
<ixz unit="SLUG*FT2"> 0 </ixz>
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS"> 376330 </emptywt>
<location name="CG" unit="IN">
<x> 1243.4 </x>
<y> 0 </y>
<z> -69.6 </z>
</location>
<pointmass name="payload">
<weight unit="LBS"> 92270 </weight>
<location name="payload" unit="IN">
<x> 1415 </x>
<y> 0 </y>
<z> -69.6 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<documentation>
- gear height determined by 3D model, supposed at scale.
- additonal contact points for crash detection, when gear retracted.
</documentation>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> 305 </x>
<y> 0 </y>
<z> -225 </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"> 249900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 83300 </damping_coeff>
<max_steer unit="DEG"> 70 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_WING">
<location unit="IN">
<x> 1252.5 </x>
<y> -216.5 </y>
<z> -225 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_BODY">
<location unit="IN">
<x> 1373.5 </x>
<y> -75.5 </y>
<z> -225 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 13 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_BODY">
<location unit="IN">
<x> 1373.5 </x>
<y> 75.5 </y>
<z> -225 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 13 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_WING">
<location unit="IN">
<x> 1252 </x>
<y> 216.5 </y>
<z> -225 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE_TIP">
<location unit="FT">
<x> 0 </x>
<y> 0 </y>
<z> 0 </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"> 249900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 83300 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_TIP">
<location unit="FT">
<x> 153.0 </x>
<y> -97.83 </y>
<z> 0 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="RIGHT_TIP">
<location unit="FT">
<x> 153.0 </x>
<y> 97.83 </y>
<z> 0 </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"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="TAIL_TIP">
<location unit="FT">
<x> 225.17 </x>
<y> 0 </y>
<z> 0 </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"> 249900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 83300 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="JT9D-7R4G2">
<location unit="IN">
<x> 1530.21 </x>
<y> -838 </y> <!-- aeromatic -391.34 -->
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>5</feed>
<thruster file="direct">
<location unit="IN">
<x> 1530.21 </x>
<y> -838 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="JT9D-7R4G2">
<location unit="IN">
<x> 1530.21 </x>
<y> -477 </y> <!-- aeromatic -391.34 -->
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>5</feed>
<thruster file="direct">
<location unit="IN">
<x> 1530.21 </x>
<y> -477 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="JT9D-7R4G2">
<location unit="IN">
<x> 1530.21 </x>
<y> 477 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>3</feed>
<feed>4</feed>
<feed>6</feed>
<thruster file="direct">
<location unit="IN">
<x> 1530.21 </x>
<y> 477 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="JT9D-7R4G2">
<location unit="IN">
<x> 1530.21 </x>
<y> 838 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>3</feed>
<feed>4</feed>
<feed>6</feed>
<thruster file="direct">
<location unit="IN">
<x> 1530.21 </x>
<y> 838 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<documentation>
- tank arm and lateral position is a guess : must fit inside the wing,
in front of gear well; and close of aero reference point to minimize the CG shift.
- typical quantities (52340 US gal).
- extended range fuel (2048 US gal), spread on the reserve tanks.
- 1 US gal = 6.7 lb.
- reference length is 229 ft 2 in (includes elevator).
- reference width is 195 ft 8 in (wing span)
</documentation>
<tank type="FUEL"> <!-- Tank number 0 -->
<documentation>
- center wing : 17160 US gal, 39/100 length (wing);
- as the tanks are emptying, CG shifts aft.
</documentation>
<location unit="IN">
<x> 1075.5 </x>
<y> 0 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 114972 </capacity>
<contents unit="LBS"> 114972 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 1 -->
<documentation>
main 1 and 4 : 4490 US gal, 48/100 length, 21/84 width.
</documentation>
<location unit="IN">
<x> 1320 </x>
<y> -587 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 30083 </capacity>
<contents unit="LBS"> 30083 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 2 -->
<documentation>
main 2 and 3 : 12570 US gal, 43/100 length, 10/84 width.
</documentation>
<location unit="IN">
<x> 1182.5 </x>
<y> -279.5 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 84219 </capacity>
<contents unit="LBS"> 84219 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 3 -->
<location unit="IN">
<x> 1182.5 </x>
<y> 279.5 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 84219 </capacity>
<contents unit="LBS"> 84219 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 4 -->
<location unit="IN">
<x> 1320 </x>
<y> 587 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 30083 </capacity>
<contents unit="LBS"> 30083 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 5 -->
<documentation>
reserve 1 and 4 : 530 + 1024 US gal, 45/100 length, 16/84 width.
</documentation>
<location unit="IN">
<x> 1237.5 </x>
<y> -447.2 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 10412 </capacity>
<contents unit="LBS"> 10412 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 6 -->
<location unit="IN">
<x> 1237.5 </x>
<y> 447.2 </y>
<z> -69.555 </z>
</location>
<capacity unit="LBS"> 10412 </capacity>
<contents unit="LBS"> 10412 </contents>
</tank>
</propulsion>
<system name="Nose Wheel Steering">
<channel name="Nose Wheel Steering">
<scheduled_gain name="systems/NWS/pedal-cmd">
<documentation>
default is rudder pedal (flight).
</documentation>
<input>fcs/rudder-cmd-norm</input>
<table>
<independentVar lookup="row">systems/NWS/engaged</independentVar>
<tableData>
0 1.0
1 0.0
</tableData>
</table>
<output>fcs/rudder-pedal-norm</output>
</scheduled_gain>
<scheduled_gain name="systems/NWS/steer-cmd">
<documentation>
default is no wheel steering (flight).
</documentation>
<input>fcs/rudder-cmd-norm</input>
<table>
<independentVar lookup="row">systems/NWS/engaged</independentVar>
<tableData>
0 0.0
1 -1.0
</tableData>
</table>
<output>fcs/steer-cmd-norm</output>
</scheduled_gain>
</channel>
</system>
<system name="Tractor">
<channel name="Tractor">
<switch name="systems/pushback/linked">
<default value="-1"/>
<test value="0">
/sim/model/pushback/position-norm gt 0.95
/gear/gear/wow == 1
gear/unit[0]/wheel-speed-fps lt 50
</test>
</switch>
<summer name="systems/pushback/speed-error">
<input>/sim/model/pushback/target-speed-fps</input>
<input>-gear/unit[0]/wheel-speed-fps</input>
</summer>
<pid name="systems/pushback/force">
<input>systems/pushback/speed-error</input>
<kp>/sim/model/pushback/kp</kp>
<ki>/sim/model/pushback/ki</ki>
<kd>/sim/model/pushback/kd</kd>
<trigger>systems/pushback/linked</trigger>
<output>/sim/model/pushback/force</output>
</pid>
<switch name="systems/pushback/force-output">
<default value="0"/>
<test value="systems/pushback/force">
systems/pushback/linked == 0
</test>
<output>external_reactions/tractor/magnitude</output>
</switch>
</channel>
</system>
<flight_control name="747-200">
<property>fcs/LE-flap-cmd-norm</property>
<property value="0">fcs/aeromatic</property>
<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>
<range>
<min>-0.35</min>
<max>0.3</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>
<range>
<min>-0.35</min>
<max>0.35</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>
<range>
<min>-0.35</min>
<max>0.35</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>
<summer name="Differential inboard aileron rad">
<documentation>
added for CR D-2144.
</documentation>
<input>fcs/left-aileron-pos-rad</input>
<input>-fcs/right-aileron-pos-rad</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-pedal-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 2.0000
</tableData>
</table>
</scheduled_gain>
<scheduled_gain name="Yaw Damper Beta">
<input>aero/beta-rad</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 0.0000
</tableData>
</table>
</scheduled_gain>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min>-0.2000</min>
<max>0.2000</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
2.9900 0.0000
3.0000 1.0000
</tableData>
</table>
</scheduled_gain>
<summer name="Rudder Sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min>-1.0000</min>
<max>1.0000</max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-sum</input>
<range>
<min>-0.3500</min>
<max>0.3500</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder Position Normalizer">
<input>fcs/rudder-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>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>5.0000</position>
<time>3.0000</time>
</setting>
<setting>
<position>10.0000</position>
<time>2.0000</time>
</setting>
<setting>
<position>20.0000</position>
<time>3.0000</time>
</setting>
<setting>
<position>25.0000</position>
<time>2.0000</time>
</setting>
<setting>
<position>30.0000</position>
<time>2.0000</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="Flap Position Normalizer">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>30</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>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>1.0000</position>
<time>12.0000</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
<kinematic name="Speedbrake Control">
<input>fcs/speedbrake-cmd-norm</input>
<traverse>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>1.0000</position>
<time>1.0000</time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
<kinematic name="Spoiler Control">
<documentation>
added : 35 deg.
</documentation>
<input>fcs/spoiler-cmd-norm</input>
<traverse>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>0.6110</position>
<time>5.0000</time>
</setting>
</traverse>
<output>fcs/spoiler-pos-rad</output>
</kinematic>
<aerosurface_scale name="Spoiler Position Normalizer">
<documentation>
added.
</documentation>
<input>fcs/spoiler-pos-rad</input>
<domain>
<min>0</min>
<max>0.6110</max>
</domain>
<range>
<min>0</min>
<max>1</max>
</range>
<output>fcs/spoiler-pos-norm</output>
</aerosurface_scale>
<kinematic name="Leading Edge Flaps Control">
<input>fcs/LE-flap-cmd-norm</input>
<traverse>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>0.6670</position>
<time>7.0000</time>
</setting>
<setting>
<position>1.0000</position>
<time>3.0000</time>
</setting>
</traverse>
<output>fcs/LE-flap-pos-norm</output>
</kinematic>
</channel>
<channel name="Gear">
<deadband name="Turn Body Gear Left">
<input>fcs/steer-pos-deg[0]</input>
<width>40</width>
<gain>0.26</gain>
<output>fcs/steer-pos-deg[2]</output>
</deadband>
<deadband name="Turn Body Gear Right">
<input>fcs/steer-pos-deg[0]</input>
<width>40</width>
<gain>0.26</gain>
<output>fcs/steer-pos-deg[3]</output>
</deadband>
</channel>
</flight_control>
<aerodynamics>
<documentation>
created :
- help takeoff.
- smooth landing.
</documentation>
<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 1.2000
0.1000 1.1500
0.1500 1.0900
0.2000 1.0200
1.1000 1.0000
</tableData>
</table>
</function>
<axis name="DRAG">
<documentation>
- replaced by CR D-2144 + CDAlpha : see formula above.
</documentation>
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">fcs/aeromatic</independentVar>
<independentVar lookup="table">atmosphere/density-altitude</independentVar>
<tableData breakPoint="0">
0 1
0.20 0.0294 0.0170
0.25 -0.0020 0.0170
0.45 0.0075 0.0170
0.65 0.0170 0.0170
</tableData>
<tableData breakPoint="20000">
0 1
0.50 0.0035 0.0170
0.65 0.0143 0.0170
0.80 0.0055 0.0170
</tableData>
<tableData breakPoint="40000">
0 1
0.70 -0.0474 0.0170
0.80 0.0109 0.0170
0.90 -0.0030 0.0170
</tableData>
</table>
<!--
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.5700 1.5000
-0.2600 0.0340
0.0000 0.0170
0.2600 0.0340
1.5700 1.5000
</tableData>
</table>
-->
</product>
</function>
<documentation>
- added from CR D-2144.
- drag is always positiv.
</documentation>
<function name="aero/coefficient/CDalpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs>
<property>aero/alpha-rad</property>