MD11.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="MD11" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> Unknown </author>
        <filecreationdate> 2003-01-01 </filecreationdate>
        <version> $Revision: 1.10 $ </version>
        <description> McDonnell Douglas MD-11 </description>
      <note>
        This model was created using publicly available data, publicly available
        technical reports, textbooks, and guesses. It contains no proprietary or
        restricted data. If this model has been validated at all, it would be
        only to the extent that it seems to "fly right", and that it possibly
        complies with 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>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 3648 </wingarea>
        <wingspan unit="FT"> 169.5 </wingspan>
        <chord unit="FT"> 21.52 </chord>
        <htailarea unit="FT2"> 912 </htailarea>
        <htailarm unit="FT"> 90.37 </htailarm>
        <vtailarea unit="FT2"> 729.6 </vtailarea>
        <vtailarm unit="FT"> 0 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 1325.5 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 168.7 </x>
            <y> -30 </y>
            <z> 75 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 1.3185e+07 </ixx>
        <iyy unit="SLUG*FT2"> 3.83816e+07 </iyy>
        <izz unit="SLUG*FT2"> 5.56127e+07 </izz>
        <emptywt unit="LBS"> 378300 </emptywt>
        <location name="CG" unit="IN">
            <x> 1325.5 </x>
            <y> 0 </y>
            <z> -60.2 </z>
        </location>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE_LG">
            <location unit="IN">
                <x> 313.3 </x>
                <y> 0 </y>
                <z> -289.2 </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"> 189150 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 63050 </damping_coeff>
            <max_steer unit="DEG"> 60 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="IN">
                <x> 1378.5 </x>
                <y> -183.1 </y>
                <z> -289.2 </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"> 630500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 126100 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MLG">
            <location unit="IN">
                <x> 1378.5 </x>
                <y> 183.1 </y>
                <z> -289.2 </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"> 630500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 126100 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
    </ground_reactions>
    <propulsion>
        <engine file="CF6-80C2">
            <location unit="IN">
                <x> 1325.48 </x>
                <y> -339 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1325.48 </x>
                    <y> -339 </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="CF6-80C2">
            <location unit="IN">
                <x> 140.83 </x>
                <y> 0 </y>
                <z> 60 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>1</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 140.83 </x>
                    <y> 0 </y>
                    <z> 60 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="CF6-80C2">
            <location unit="IN">
                <x> 1325.48 </x>
                <y> 339 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>2</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1325.48 </x>
                    <y> 339 </y>
                    <z> -40 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <tank type="FUEL">    <!-- Tank number 0 -->
            <location unit="IN">
                <x> 1325.48 </x>
                <y> 0 </y>
                <z> -60.249 </z>
            </location>
            <capacity unit="LBS"> 9851.6 </capacity>
            <contents unit="LBS"> 4925.8 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 -->
            <location unit="IN">
                <x> 1325.48 </x>
                <y> 0 </y>
                <z> -60.249 </z>
            </location>
            <capacity unit="LBS"> 9851.6 </capacity>
            <contents unit="LBS"> 4925.8 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 2 -->
            <location unit="IN">
                <x> 1325.48 </x>
                <y> 0 </y>
                <z> -60.249 </z>
            </location>
            <capacity unit="LBS"> 9851.6 </capacity>
            <contents unit="LBS"> 4925.8 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 3 -->
            <location unit="IN">
                <x> 1325.48 </x>
                <y> 0 </y>
                <z> -60.249 </z>
            </location>
            <capacity unit="LBS"> 9851.6 </capacity>
            <contents unit="LBS"> 4925.8 </contents>
        </tank>
    </propulsion>
    <flight_control name="FCS: MD11">
        <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>
        </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="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>
        </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>
                        3.00  0.00
                       11.00  2.00
                    </tableData>
                </table>
            </scheduled_gain>

            <scheduled_gain name="Yaw Damper Beta">
                <input>aero/beta-rad</input>
                <table>
                    <independentVar>aero/qbar-psf</independentVar>
                    <tableData>
                        3.00  0.00
                       11.00  0.00
                    </tableData>
                </table>
            </scheduled_gain>

            <summer name="Yaw Damper Sum">
                <input>fcs/yaw-damper-beta</input>
                <input>fcs/yaw-damper-rate</input>
                <clipto>
                    <min>-0.2</min>
                    <max>0.2</max>
                </clipto>
            </summer>

            <scheduled_gain name="Yaw Damper Final">
                <input>fcs/yaw-damper-sum</input>
                <table>
                    <independentVar>aero/qbar-psf</independentVar>
                    <tableData>
                        2.99  0.00
                        3.00  1.00
                    </tableData>
                </table>
            </scheduled_gain>

            <summer name="Rudder Sum">
                <input>fcs/rudder-command-sum</input>
                <input>fcs/yaw-damper-final</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Rudder Control">
                <input>fcs/rudder-sum</input>
                <range>
                    <min>-0.35</min>
                    <max>0.35</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>
        </channel>
        <channel name="Flaps">
            <kinematic name="Flaps Control">
                <input>fcs/flap-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>15</position>
                        <time>4</time>
                    </setting>
                    <setting>
                        <position>30</position>
                        <time>3</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>  <!-- Flaps actual minimum position -->
                <max>30</max>  <!-- Flaps actual maximum position -->
              </domain>
              <range>
                <min>0</min>  <!-- Flaps normalized minimum position -->
                <max>1</max>  <!-- Flaps normalized maximum position -->
              </range>
              <output>fcs/flap-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <channel name="Landing Gear">
            <kinematic name="Gear Control">
                <input>gear/gear-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>5</time>
                    </setting>
                </traverse>
                <output>gear/gear-pos-norm</output>
            </kinematic>
        </channel>
        <channel name="Speedbrake">
            <kinematic name="Speedbrake Control">
                <input>fcs/speedbrake-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>fcs/speedbrake-pos-norm</output>
            </kinematic>
        </channel>
    </flight_control>
    <aerodynamics>

        <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	0.0380
                              0.0000	0.0190
                              0.2600	0.0380
                              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>
            <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>0.0570</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>0.0130</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>0.0190</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>
            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/elevator-pos-norm</property>
                    <value>0.0570</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">
            <function name="aero/coefficient/CLalpha">
                <description>Lift_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.2000	-0.6800
                              0.0000	0.2000
                              0.2300	1.2000
                              0.6000	0.6000
                          </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>
                    <property>fcs/flap-pos-norm</property>
                    <value>1.5000</value>
                </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>-0.0900</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>-0.6000</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	-1.2000
                              2.0000	-0.3000
                          </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>-17.0000</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>-6.0000</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>