<?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> 30 May 2009 </filecreationdate>
        <version> 1.02 </version>
        <description> 747-200 with JT9D-7R4G2 </description>
        <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>

        <limitation>steering of body gear has no hysteresis.</limitation>
        <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>
    </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>

    <flight_control name="747-200">
     <property>fcs/LE-flap-cmd-norm</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>

     </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>

        <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>
    </flight_control>
    <aerodynamics>
        <documentation>
             created :
             - help takeoff.
             - smooth landing.
        </documentation>
        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <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>
            </product>
        </function>

        <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>
                      <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>
            <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>
                    <value>0.0420</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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.0000	
                              0.7900	0.0000	
                              1.1000	0.0230	
                              1.8000	0.0150	
                          </tableData>
                      </table>
                </product>
            </function>
            <documentation>
              - 0.055 -> 0.050.
              - 0.005 for LE flaps.
            </documentation>
            <function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>0.0500</value>
                </product>
            </function>
            <documentation>
              added.
            </documentation>
            <function name="aero/coefficient/CDLEflap">
                <description>Drag_due_to_leading_edge_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/LE-flap-pos-norm</property>
                    <value>0.0050</value>
                </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>0.0110</value>
                </product>
            </function>
            <documentation>
              no speedbrake : 0.0170 -> 0.0.
            </documentation>
            <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>0.0</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>aero/beta-rad</independentVar>
                          <tableData>
                              -1.5700	1.2300	
                              -0.2600	0.0500	
                              0.0000	0.0000	
                              0.2600	0.0500	
                              1.5700	1.2300	
                          </tableData>
                      </table>
                </product>
            </function>
            <documentation>
              no negativ drag : 0.0550 -> 0.0055.
            </documentation>
            <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>0.0055</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>-1.0000</value>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <documentation>
              add Mach 0.2 : without flaps, 290 kt to climb at full load.
            </documentation>
            <function name="aero/coefficient/CLalpha">
                <description>Lift_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">velocities/mach</independentVar>
                          <tableData>
                                       0.2000   0.6000	
                             -0.200   -0.3400  -0.6800	
                              0.0000   0.0000   0.2000	
                              0.2300   0.6000   1.2000	
                              0.6000   0.3000   0.6000	
                          </tableData>
                      </table>
                </product>
            </function>

            <documentation>
              - added.
              - leading edge flaps enables higher alpha (by wing shape);
                while trailing edge flaps enables lower speed (by more lift).
            </documentation>
            <function name="aero/coefficient/dCLLEflap">
                <description>Delta_Lift_due_to_leading_edge_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/LE-flap-pos-norm</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              0.0000   0.0000
                              0.2000   0.1000
                              0.3000   0.1500
                              0.6000   0.0000
                          </tableData>
                      </table>
                </product>
            </function>

            <documentation>
              aero/qbar-psf|metrics/Sw-sqft|fcs/flap-pos-norm

              aeromatic was 1.5 :
              - reduces landing flaps lift, to respect VREF 154 kt : obliged to reduce the lift at 30 deg.
              - keeps takeoff flaps lift, to respect V2 190 kt.
              - includes the flaps inside the ground effect, to get more lift.
            </documentation>
            <function name="aero/coefficient/dCLflap">
                <description>Delta_Lift_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000	
                              20.0000	1.0000	
                              30.0000	0.9100	
                          </tableData>
                      </table>
                </product>
            </function>

            <documentation>
              no speedbrake : -0.08 -> 0.0.
            </documentation>
            <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>0.0000</value>
                </product>
            </function>

            <documentation>
              added.
            </documentation>
            <function name="aero/coefficient/dCLsp">
                <description>Delta_Lift_due_to_spoilers</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/spoiler-pos-norm</property>
                    <value>-1.0000</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>0.2000</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>-0.1000</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>-0.4000</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>0.1500</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>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1000	
                              2.0000	0.0330	
                          </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>0.0100</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>-0.7000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <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>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-1.3000	
                              2.0000	-0.3250	
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cmq">
                <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>-21.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmadot">
                <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>-4.0000</value>
                </product>
            </function>
        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <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>0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnr">
                <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>-0.1500</value>
                </product>
            </function>
            <function name="aero/coefficient/Cndr">
                <description>Yaw_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>-0.1000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <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>0.0000</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
</fdm_config>
