<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="1970 Boeing 747 100B" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author>Darren Jones</author>
        <email>darrenpauljones@hotmail.com</email>
        <organization>Department of Mechanical Engineering,
                      University of Bath,
                      UK                                    </organization>
        <filecreationdate>2003-01-01 </filecreationdate>
        <version>1.0</version>
        <description> Models a 1970 Boeing 747-100B with Pratt and Whitney JT9D-3
                      turbofan engines                      </description>
        <note>Since a moving stabilizer property is not available the
              speedbrake property is being used to emulate the Boeing
              747 trimmable horizontal stabilizer.</note>
        <note>Aircraft origin for measurements is the nose.</note>
        <limitation>Aerodynamic effects of undercarriage not modelled</limitation>
        <limitation>Undercarriage data approximated</limitation>
        <limitation>Spoilers not modeled</limitation>
        <reference refID="None" author="Hanke, C.R." title="The Simulation of a Large Jet Transport Aircraft, Vol I: Mathematical Model" date="1970"/>
        <reference refID="None" author="Hanke, C.R." title="The Simulation of a Large Jet Transport Aircraft, Vol II: Modeling Data" date="1970"/>
        <reference refID="None" author="Roskam, J." title="Airplane Flight Dynamics and Automatic Flight Control, Vol I" date="1979"/>
        <reference refID="None" author="Jane's" title="Jane's All The World's Aircraft 1980-1981" date="1981"/>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 5500 </wingarea>
        <wingspan unit="FT"> 195.7 </wingspan>
        <chord unit="FT"> 27.3 </chord>
        <htailarea unit="FT2"> 1470 </htailarea>
        <htailarm unit="FT"> 99 </htailarm>
        <vtailarea unit="FT2"> 830 </vtailarea>
        <vtailarm unit="FT"> 0 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 1340 </x>
            <y> 0 </y>
            <z> -39 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 236 </x>
            <y> -40 </y>
            <z> 118 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 1340 </x>
            <y> 0 </y>
            <z> -39 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 1.842e+07 </ixx>
        <iyy unit="SLUG*FT2"> 2.528e+07 </iyy>
        <izz unit="SLUG*FT2"> 5.298e+07 </izz>
        <ixz unit="SLUG*FT2"> -940000 </ixz>
        <emptywt unit="LBS"> 370000 </emptywt>
        <location name="CG" unit="IN">
            <x> 1340 </x>
            <y> 0 </y>
            <z> -39 </z>
        </location>
        <pointmass name="name">
            <weight unit="LBS"> 95500 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 1455 </x>
                <y> 0 </y>
                <z> -39 </z>
            </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="IN">
                <x> 305 </x>
                <y> 0 </y>
                <z> -222 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 15000 </damping_coeff>
            <max_steer unit="DEG"> 10 </max_steer>
            <brake_group> NOSE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="FWD_LEFT">
            <location unit="IN">
                <x> 1313 </x>
                <y> -217 </y>
                <z> -222 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="REAR_LEFT">
            <location unit="IN">
                <x> 1434 </x>
                <y> -76 </y>
                <z> -222 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="REAR_RIGHT">
            <location unit="IN">
                <x> 1434 </x>
                <y> 76 </y>
                <z> -222 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="FWD_RIGHT">
            <location unit="IN">
                <x> 1313 </x>
                <y> 217 </y>
                <z> -222 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="TAIL_TIP">
            <location unit="IN">
                <x> 2635 </x>
                <y> 0 </y>
                <z> 48 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="ENG_LEFT">
            <location unit="IN">
                <x> 915 </x>
                <y> -477 </y>
                <z> -166 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="ENG_RIGHT">
            <location unit="IN">
                <x> 915 </x>
                <y> 477 </y>
                <z> -166 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="W_TIP_LEFT">
            <location unit="IN">
                <x> 1719 </x>
                <y> -1137 </y>
                <z> 42 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="W_TIP_RIGHT">
            <location unit="IN">
                <x> 1719 </x>
                <y> -1137 </y>
                <z> 42 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="NOSE_TIP">
            <location unit="IN">
                <x> 277 </x>
                <y> 0 </y>
                <z> -97 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 2e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
        </contact>
    </ground_reactions>
    <propulsion>
        <engine file="JT9D-3">
            <location unit="IN">
                <x> 1375 </x>
                <y> -839 </y>
                <z> -47 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.044 </pitch>
                <yaw> -0.035 </yaw>
            </orient>
            <feed>0</feed>
            <feed>1</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1525 </x>
                    <y> -839 </y>
                    <z> -47 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="JT9D-3">
            <location unit="IN">
                <x> 1044 </x>
                <y> -477 </y>
                <z> -95 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.044 </pitch>
                <yaw> -0.035 </yaw>
            </orient>
            <feed>1</feed>
            <feed>2</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1194 </x>
                    <y> -477 </y>
                    <z> -95 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="JT9D-3">
            <location unit="IN">
                <x> 1044 </x>
                <y> 477 </y>
                <z> -95 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.044 </pitch>
                <yaw> 0.035 </yaw>
            </orient>
            <feed>2</feed>
            <feed>3</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1194 </x>
                    <y> 477 </y>
                    <z> -95 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="JT9D-3">
            <location unit="IN">
                <x> 1375 </x>
                <y> 839 </y>
                <z> -47 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.044 </pitch>
                <yaw> 0.035 </yaw>
            </orient>
            <feed>3</feed>
            <feed>4</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1525 </x>
                    <y> 839 </y>
                    <z> -47 </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> 1590 </x>
                <y> -749 </y>
                <z> -28 </z>
            </location>
            <capacity unit="LBS"> 25000 </capacity>
            <contents unit="LBS"> 25000 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 -->
            <location unit="IN">
                <x> 1340 </x>
                <y> -362 </y>
                <z> -57 </z>
            </location>
            <capacity unit="LBS"> 75000 </capacity>
            <contents unit="LBS"> 75000 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 2 -->
            <location unit="IN">
                <x> 1165 </x>
                <y> 0 </y>
                <z> -84 </z>
            </location>
            <capacity unit="LBS"> 80000 </capacity>
            <contents unit="LBS"> 80000 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 3 -->
            <location unit="IN">
                <x> 1340 </x>
                <y> 362 </y>
                <z> -57 </z>
            </location>
            <capacity unit="LBS"> 75000 </capacity>
            <contents unit="LBS"> 75000 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 4 -->
            <location unit="IN">
                <x> 1590 </x>
                <y> 749 </y>
                <z> -28 </z>
            </location>
            <capacity unit="LBS"> 25000 </capacity>
            <contents unit="LBS"> 25000 </contents>
        </tank>
    </propulsion>
    <flight_control name="FCS: boeing747-jsbsim">

        <channel name="Pitch">
            <summer name="Elevator Input">
                <input>fcs/elevator-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/elevator-input</input>
                <gain>0.0175</gain>
                <range>
                    <min>-25</min>
                    <max>15</max>
                </range>
            </aerosurface_scale>

            <summer name="Elevator Summer">
                <input>fcs/elevator-control</input>
    <!--            <input>fcs/elevator-fix-pos</input> -->
                <output>fcs/elevator-pos-rad</output>
            </summer>

            <summer name="Stabilizer Input">
                <input>fcs/pitch-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Stabilizer Control">
                <input>fcs/stabilizer-input</input>
                <gain>0.01745</gain>
                <range>
                    <min>-12</min>
                    <max>3</max>
                </range>
                <output>fcs/speedbrake-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>
                <gain>0.01745</gain>
                <range>
                    <min>-25</min>
                    <max>25</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Control">
                <input>-fcs/roll-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-25</min>
                    <max>25</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>

        </channel>
        <channel name="Yaw">

            <pure_gain name="Yaw Damper Rate">
                <input>velocities/r-rad_sec</input>
                <gain>2.5</gain>
            </pure_gain>

            <summer name="Yaw Trim Sum">
                <input>fcs/rudder-cmd-norm</input>
                <input>fcs/yaw-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <summer name="Rudder Sum">
                <input>fcs/yaw-trim-sum</input>
                <input>fcs/yaw-damper-rate</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Rudder Control">
                <input>fcs/rudder-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-25</min>
                    <max>25</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>10</position>
                        <time>3</time>
                    </setting>
                    <setting>
                        <position>20</position>
                        <time>2</time>
                    </setting>
                    <setting>
                        <position>30</position>
                        <time>2</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 control">
            <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>
    </flight_control>

    <aerodynamics>
        <function name="aero/function/kCDge">
            <description>Change_in_drag_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	0.0480
                          8.0000	0.5150
                          16.0000	0.7090
                          24.0000	0.8150
                          32.0000	0.8820
                          40.0000	0.9280
                          48.0000	0.9620
                          56.0000	0.9880
                          64.0000	1.0000
                          72.0000	1.0000
                          80.0000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>
        <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	1.2030
                          8.0000	1.1270
                          16.0000	1.0730
                          24.0000	1.0460
                          32.0000	1.0250
                          40.0000	1.0190
                          48.0000	1.0130
                          56.0000	1.0080
                          64.0000	1.0060
                          72.0000	1.0020
                          80.0000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <axis name="DRAG">
            <function name="aero/coefficient/CDo">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.0220
                              0.2000	0.0200
                              0.6500	0.0220
                              0.9000	0.0240
                              0.9700	0.0500
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDDf">
                <description>Delta_drag_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000
                              10.0000	0.0120
                              20.0000	0.0310
                              30.0000	0.0850
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDwbh">
                <description>Drag_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/alpha-rad</property>
                    <property>aero/function/kCDge</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.2000	1.1300
                              0.6500	0.2000
                              0.9000	0.5000
                          </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/mag-elevator-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.2000	0.0000
                              0.6500	0.0000
                              0.9000	0.0000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/mag-beta-rad</property>
                      <table>
                          <independentVar>aero/qbar-psf</independentVar>
                          <tableData>
                              0.0000	-0.0600
                              0.2000	-0.0600
                              0.6500	-0.0600
                              0.9000	-0.0600
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.9500
                              0.2000	-0.9300
                              0.6500	-0.9100
                              0.9000	-0.8900
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYda">
                <description>Side_force_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.2000	0.0000
                              0.6500	0.0000
                              0.9000	0.0000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYdr">
                <description>Side_force_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/rudder-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1700
                              0.2000	0.1600
                              0.6500	0.1100
                              0.9000	0.0600
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYp">
                <description>Side_force_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.4000
                              0.2000	0.4000
                              0.6500	0.4000
                              0.9000	0.1000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYr">
                <description>Side_force_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1750
                              0.2000	0.1700
                              0.6500	0.1490
                              0.9000	0.1510
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <function name="aero/coefficient/CLo">
                <description>Lift_at_zero_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1100
                              0.2000	0.1800
                              0.6500	0.2300
                              0.9000	0.3000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLwbh">
                <description>Lift_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/alpha-rad</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	5.4000
                              0.2000	5.4000
                              0.6500	5.3000
                              0.9000	5.4000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLDf">
                <description>Delta_lift_due_to_flap_deflection</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
                              10.0000	0.1000
                              20.0000	0.3300
                              30.0000	0.7800
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.4100
                              0.2000	0.3600
                              0.6500	0.3200
                              0.9000	0.3000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLs">
                <description>Lift_due_to_stabilizer_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.8190
                              0.2000	0.7850
                              0.6500	0.7390
                              0.9000	0.8590
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLadot">
                <description>Lift_due_to_alpha_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/alphadot-rad_sec</property>
                    <property>aero/ci2vel</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	6.7000
                              0.2000	6.7000
                              0.6500	6.5000
                              0.9000	5.5000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLq">
                <description>Lift_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	6.8000
                              0.2000	5.6500
                              0.6500	5.1000
                              0.9000	6.9000
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.1400
                              0.2000	-0.1400
                              0.6500	-0.1700
                              0.9000	-0.1400
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate_(roll_damping)</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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.3500
                              0.2000	-0.3300
                              0.6500	-0.2800
                              0.9000	-0.2600
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1500
                              0.2000	0.1400
                              0.6500	0.1600
                              0.9000	0.2300
                          </tableData>
                      </table>
                </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	0.0802
                              0.2000	0.0773
                              0.6500	0.0638
                              0.9000	0.0682
                          </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.0080
                              0.2000	0.0070
                              0.6500	0.0050
                              0.9000	0.0030
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmo">
                <description>Pitching_moment_at_zero_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1000
                              0.2000	0.0900
                              0.6500	0.0300
                              0.9000	0.0150
                          </tableData>
                      </table>
                </product>
            </function>
            <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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-1.5000
                              0.2000	-1.3600
                              0.6500	-1.0100
                              0.9000	-0.9800
                          </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-22.6000
                              0.2000	-21.4000
                              0.6500	-20.3000
                              0.9000	-25.2000
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-3.4000
                              0.2000	-3.2000
                              0.6500	-3.9000
                              0.9000	-8.8000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator_deflection</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	-1.6000
                              0.2000	-1.4000
                              0.6500	-1.3000
                              0.9000	-1.2000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cms">
                <description>Pitch_moment_due_to_stabilizer_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/speedbrake-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-3.1000
                              0.2000	-2.9200
                              0.6500	-2.7500
                              0.9000	-3.2100
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cmdf">
                <description>Delta_pitching_moment_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000
                              10.0000	0.0000
                              20.0000	-0.0800
                              30.0000	-0.1600
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1600
                              0.2000	0.1500
                              0.6500	0.1500
                              0.9000	0.2000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnp">
                <description>Yaw_moment_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.0250
                              0.2000	-0.0250
                              0.6500	-0.0250
                              0.9000	-0.0250
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.2500
                              0.2000	-0.2400
                              0.6500	-0.2500
                              0.9000	-0.3100
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Yaw_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	0.0070
                              0.2000	0.0070
                              0.6500	0.0040
                              0.9000	-0.0050
                          </tableData>
                      </table>
                </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>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-0.1050
                              0.2000	-0.1020
                              0.6500	-0.0890
                              0.9000	-0.0780
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>
    </aerodynamics>
    <output name="JSBout747.csv" type="CSV" rate="5">
        <simulation> OFF </simulation>
        <atmosphere> OFF </atmosphere>
        <massprops> ON </massprops>
        <rates> ON </rates>
        <velocities> ON </velocities>
        <forces> ON </forces>
        <moments> ON </moments>
        <position> ON </position>
        <propulsion> ON </propulsion>
        <aerosurfaces> OFF </aerosurfaces>
        <fcs> OFF </fcs>
        <ground_reactions> OFF </ground_reactions>
        <coefficients> OFF </coefficients>
    </output>
</fdm_config>
