<?xml version="1.0"?>
<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?>
<fdm_config name="Victor" version="2.0" release="ALPHA">

    <fileheader>
        <author> Alex Park </author>
        <filecreationdate> 01/03/2009 </filecreationdate>
        <description>
Handley page Victor tanker K2        </description>
        <version> 0.1 </version>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 2597 </wingarea>
        <wingspan unit="FT"> 120 </wingspan>
        <chord unit="FT"> 35.73 </chord>
        <wing_incidence unit=""> 2 </wing_incidence>
        <htailarea unit="FT2"> 991.46 </htailarea>
        <htailarm unit="FT"> 44.96 </htailarm>
        <vtailarea unit="FT2"> 793.17 </vtailarea>
        <vtailarm unit="FT"> 44.96 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 659.38 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 83.92 </x>
            <y> -32 </y>
            <z> 80 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2">1.19898e+006</ixx>
        <iyy unit="SLUG*FT2">1.0968e+006</iyy>
        <izz unit="SLUG*FT2">2.33473e+006</izz>
        <ixz unit="SLUG*FT2">0</ixz>
        <iyz unit="SLUG*FT2">0</iyz>
        <ixy unit="SLUG*FT2">0</ixy>
        <emptywt unit="LBS">122378</emptywt>
        <location name="CG" unit="IN">
            <x>659.38</x>
            <y>0</y>
            <z>-29.97</z>
        </location>
        <pointmass name="dummy">
            <weight unit="LBS">1</weight>
            <location unit="IN">
                <x>659.38</x>
                <y>0</y>
                <z>-29.97</z>
            </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="IN">
                <x> 380 </x>
                <y> 0 </y>
                <z> -113.78 </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"> 61188.8 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20396.3 </damping_coeff>
            <max_steer unit="DEG"> 10 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MAIN">
            <location unit="IN">
                <x> 747 </x>
                <y> -189 </y>
                <z> -113.7 </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"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MAIN">
            <location unit="IN">
                <x> 747 </x>
                <y> 189 </y>
                <z> -113.7 </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"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="LEFT_WING">
            <location unit="IN">
                <x> 1054 </x>
                <y> -660.5 </y>
                <z> -19.7 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_WING">
            <location unit="IN">
                <x> 1054 </x>
                <y> 660.5 </y>
                <z> -19.7 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="TAIL">
            <location unit="IN">
                <x> 1162 </x>
                <y> 0 </y>
                <z> -29 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="RUDDER">
            <location unit="IN">
                <x> 1164 </x>
                <y> 0 </y>
                <z> 211 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="NOSE">
            <location unit="IN">
                <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 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 203963 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 40792.5 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
    </ground_reactions>

    <propulsion>
        <engine file="Conway-Rco11">
            <location unit="IN">
                <x> 1064 </x>
                <y> -92 </y>
                <z> -58 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1064 </x>
                    <y> -92 </y>
                    <z> -58 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="Conway-Rco11">
            <location unit="IN">
                <x> 1064 </x>
                <y> -140 </y>
                <z> -58 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>1</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1064 </x>
                    <y> -140 </y>
                    <z> -58 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="Conway-Rco11">
            <location unit="IN">
                <x> 1064 </x>
                <y> 92 </y>
                <z> -58 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>2</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1064 </x>
                    <y> 92 </y>
                    <z> -58 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="Conway-Rco11">
            <location unit="IN">
                <x> 1064 </x>
                <y> 140 </y>
                <z> -58 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>3</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 1064 </x>
                    <y> 140 </y>
                    <z> -58 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <tank type="FUEL">
            <location unit="IN">
                <x> 759.38 </x>
                <y> -160 </y>
                <z> -29.97 </z>
            </location>
            <capacity unit="LBS">18500</capacity>
            <contents unit="LBS">15500</contents>
        </tank>
        <tank type="FUEL">
            <location unit="IN">
                <x> 759.38 </x>
                <y> -160 </y>
                <z> -29.97 </z>
            </location>
            <capacity unit="LBS">18500</capacity>
            <contents unit="LBS">15500</contents>
        </tank>
        <tank type="FUEL">
            <location unit="IN">
                <x> 759.38 </x>
                <y> 160 </y>
                <z> -29.97 </z>
            </location>
            <capacity unit="LBS">18500</capacity>
            <contents unit="LBS">15500</contents>
        </tank>
        <tank type="FUEL">
            <location unit="IN">
                <x> 759.38 </x>
                <y> 160 </y>
                <z> -29.97 </z>
            </location>
            <capacity unit="LBS">18500</capacity>
            <contents unit="LBS">15500</contents>
        </tank>
    </propulsion>

    <flight_control name="FCS: Victor">

        <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 Normalized">
                <input>fcs/elevator-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max> 0.3</max>
                </domain>
                <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="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="Left aileron Normalized">
                <input>fcs/left-aileron-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max> 0.35</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max> 1</max>
                </range>
                <output>fcs/left-aileron-pos-norm</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right aileron Normalized">
                <input>fcs/right-aileron-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max> 0.35</max>
                </domain>
                <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>
            </summer>

            <scheduled_gain name="Yaw Damper Rate">
              <input>velocities/r-aero-rad_sec</input>
              <table>
                <independentVar> velocities/ve-kts </independentVar>
                <tableData>
                  30		0
                  60		2
                </tableData>
              </table>
            </scheduled_gain>

            <scheduled_gain name="Yaw Damper Beta">
              <input>aero/beta-rad</input>
              <table>
                <independentVar> velocities/ve-kts </independentVar>
                <tableData>
                  30		0
                  60		0
                </tableData>
              </table>
            </scheduled_gain>

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

            <scheduled_gain name="Yaw Damper Final">
              <input>fcs/yaw-damper-sum</input>
              <table>
                <independentVar> velocities/ve-kts </independentVar>
                <tableData>
                  30		0
                  31		1
                </tableData>
              </table>
            </scheduled_gain>

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

            <aerosurface_scale name="Rudder Normalized">
                <input>fcs/rudder-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max> 0.35</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max> 1</max>
                </range>
                <output>fcs/rudder-pos-norm</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>0.5</position>
                  <time>4</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>3</time>
                </setting>
              </traverse>
              <output>fcs/flap-pos-norm</output>
            </kinematic>

        </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/spoiler-cmd-norm</input>
              <traverse>
                <setting>
                  <position>0</position>
                  <time>0</time>
                </setting> 
                <setting>
                  <position>0.5</position>
                  <time>1.5</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>1.5</time>
                </setting>
              </traverse>
              <output>fcs/speedbrake-pos-norm</output>
            </kinematic>

        </channel>

    </flight_control>

    <aerodynamics>
        <axis name="LIFT" unit="LBS">
            <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>
                          -0.2          -0.68       
                          0             0.2         
                          0.23          1.2         
                          0.6           0.6         
                        </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-deg</property>
                    <value>0</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>-0.08</value>
                </product>
            </function>
            <function name="aero/coefficient/CLde">
                <description>Lift_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <value>0.2</value>
                </product>
            </function>
        </axis>
        <axis name="DRAG" unit="LBS">
            <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>
                          -1.57         1.5         
                          -0.26         0.022       
                          0             0.017       
                          0.26          0.022       
                          1.57          1.5         
                        </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>0.042</value>
                </product>
            </function>
            <function name="aero/coefficient/CDmach">
                <description>Drag_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                          0             0           
                          0.79          0           
                          1.1           0.023       
                          1.8           0.015       
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-deg</property>
                    <value>0.00183</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>0.011</value>
                </product>
            </function>
            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.1</value>
                </product>
            </function>
            <function name="aero/coefficient/CDbc">
                <description>Drag_due_to_braking_chute</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>/controls/chute-pos-norm</property>
                    <value>5000</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>
                          -1.57         1.23        
                          -0.26         0.05        
                          0             0           
                          0.26          0.05        
                          1.57          1.23        
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <abs><property>fcs/elevator-pos-norm</property></abs>
                    <value>0.04</value>
                </product>
            </function>
        </axis>
        <axis name="SIDE" unit="LBS">
            <function name="aero/coefficient/CYb">
                <description>Side_force_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/beta-rad</property>
                    <value>-1</value>
                </product>
            </function>
        </axis>
        <axis name="ROLL" unit="LBS*FT">
            <function name="aero/coefficient/Clb">
                <description>Roll_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <value>-0.1</value>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <value>-0.4</value>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>0.15</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             0.1         
                          2             0.033       
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.01</value>
                </product>
            </function>
        </axis>
        <axis name="PITCH" unit="LBS*FT">
            <function name="aero/coefficient/Cmalpha">
                <description>Pitch_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                    <value>-0.7</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <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             -1.3        
                          2             -0.325      
                        </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</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</value>
                </product>
            </function>
        </axis>
        <axis name="YAW" unit="LBS*FT">
            <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>0.12</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>-0.15</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>-0.1</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</value>
                </product>
            </function>
        </axis>
    </aerodynamics>

    <output name="JSBout.csv" type="CSV" rate="100">
        <simulation> OFF </simulation>
        <atmosphere> OFF </atmosphere>
        <massprops> OFF </massprops>
        <aerosurfaces> OFF </aerosurfaces>
        <rates> OFF </rates>
        <velocities> OFF </velocities>
        <forces> OFF </forces>
        <moments> OFF </moments>
        <position> OFF </position>
        <coefficients> OFF </coefficients>
        <ground_reactions> OFF </ground_reactions>
        <fcs> OFF </fcs>
        <propulsion> OFF </propulsion>
    </output>
</fdm_config>
