T38.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="T38" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
     <author>Aeromatic v 0.8, DPC</author>
     <filecreationdate>2004-01-01</filecreationdate>
     <version>$Revision$</version>
     <description>Models a Northrop T-38</description>
 </fileheader>

<!--
  File:     T38.xml
  Inputs:
    name:          T38
    type:          two-engine transonic/supersonic fighter
    max weight:    12500.0 lb
    wing span:     25.25 ft
    length:        46.3 ft
    wing area:     170.0 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  73.53 lb/sq-ft
    CL-alpha:      3.6 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.024
    K:             0.09

-->

    <metrics>
        <wingarea unit="FT2">  170 </wingarea>
        <wingspan unit="FT">    25.25 </wingspan>
        <chord unit="FT">        6.73 </chord>
        <htailarea unit="FT2">  34 </htailarea>
        <htailarm unit="FT">    13 </htailarm>
        <vtailarea unit="FT2">  47 </vtailarea>
        <vtailarm unit="FT">    13 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 320 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 154 </x>
            <y> 0 </y>
            <z> 36 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 320 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2">  7806 </ixx>
        <iyy unit="SLUG*FT2"> 36075 </iyy>
        <izz unit="SLUG*FT2"> 31319 </izz>
        <emptywt unit="LBS">   7574 </emptywt>
        <location name="CG" unit="IN">
            <x> 314 </x>
            <y> 0 </y>
            <z> -10 </z>
        </location>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE_LG">
            <location unit="IN">
                <x> 73 </x>
                <y> 0 </y>
                <z> -46 </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"> 5000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 500 </damping_coeff>
            <max_steer unit="DEG"> 5 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="IN">
                <x> 335 </x>
                <y> -65 </y>
                <z> -46 </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"> 37870 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 3787 </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> 335 </x>
                <y> 65 </y>
                <z> -46 </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"> 37870 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 3787 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
	<contact type="STRUCTURE" name="NOSE">
	    <location unit="IN">
		<x> -22 </x>
		<y> 0 </y>
		<z> -4 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
	<contact type="STRUCTURE" name="LEFT_WINGTIP">
	    <location unit="IN">
		<x> 330 </x>
		<y> -157 </y>
		<z> -15 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
	<contact type="STRUCTURE" name="RIGHT_WINGTIP">
	    <location unit="IN">
		<x> 330 </x>
		<y> 157 </y>
		<z> -15 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
	<contact type="STRUCTURE" name="CANOPY">
	    <location unit="IN">
		<x> 178 </x>
		<y> 0 </y>
		<z> 54 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
	<contact type="STRUCTURE" name="VSTAB">
	    <location unit="IN">
		<x> 450 </x>
		<y> 0 </y>
		<z> 114 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
	<contact type="STRUCTURE" name="ENGINES">
	    <location unit="IN">
		<x> 525 </x>
		<y> 0 </y>
		<z> 5 </z>
	    </location>
	    <static_friction>  0.80 </static_friction>
	    <dynamic_friction> 0.50 </dynamic_friction>
	    <spring_coeff unit="LBS/FT">      5000.00 </spring_coeff>
	    <damping_coeff unit="LBS/FT/SEC">  500.00 </damping_coeff>
	</contact>
      </ground_reactions>
    <propulsion>
        <engine file="J85-GE-5">
            <location unit="IN">
                <x> 452 </x>
                <y> -20 </y>
                <z> 0 </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> 551 </x>
                    <y> -20 </y>
                    <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="J85-GE-5">
            <location unit="IN">
                <x> 452 </x>
                <y> 20 </y>
                <z> 0 </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> 551 </x>
                    <y> 20 </y>
                    <z> 0 </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> 298 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <capacity unit="LBS"> 1953 </capacity>
            <contents unit="LBS"> 1900 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 -->
            <location unit="IN">
                <x> 370 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <capacity unit="LBS"> 2029 </capacity>
            <contents unit="LBS"> 2000 </contents>
        </tank>
    </propulsion>
    <flight_control name="FCS: T38-FCS">
        <channel name="Pitch">
            <summer name="Pilot Pitch Sum">
                <input>fcs/elevator-cmd-norm</input>
                <input>fcs/pitch-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <scheduled_gain name="Pitch Feel">
                <input>fcs/pilot-pitch-sum</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.0000	1.0000
                        0.6000	1.0000
                        1.2000	0.7000
                    </tableData>
                </table>
            </scheduled_gain>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/pitch-feel</input>
                <range>
                    <min>-1.0</min>
                    <max>0.583</max>
                </range>
                <output>fcs/elevator-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <channel name="Roll">
            <summer name="Pilot Roll Sum">
                <input>fcs/aileron-cmd-norm</input>
                <input>fcs/roll-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <scheduled_gain name="Roll Feel">
                <input>fcs/pilot-roll-sum</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.0000	1.0000
                        0.6000	1.0000
                        1.2000	0.7000
                    </tableData>
                </table>
            </scheduled_gain>

            <aerosurface_scale name="Left Aileron Control">
                <input>fcs/roll-feel</input>
                <range>
                    <min>-1.00</min>
                    <max>0.75</max>
                </range>
                <output>fcs/left-aileron-pos-norm</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Control">
                <input>-fcs/roll-feel</input>
                <range>
                    <min>-1.00</min>
                    <max>0.65</max>
                </range>
                <output>fcs/right-aileron-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <channel name="Yaw">
            <summer name="Rudder Command Sum">
                <input>fcs/rudder-cmd-norm</input>
                <input>fcs/yaw-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <scheduled_gain name="Yaw SAS Rate">
                <input>velocities/r-aero-rad_sec</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.0000	0.0000
                        0.1000	0.0000
                        0.1100	1.0000
                    </tableData>
                </table>
            </scheduled_gain>

            <scheduled_gain name="Yaw SAS Beta">
                <input>aero/beta-rad</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.0000	0.0000
                        1.2000	0.0000
                    </tableData>
                </table>
            </scheduled_gain>

            <summer name="Yaw SAS Sum">
                <input>fcs/yaw-sas-rate</input>
                <input>fcs/yaw-sas-beta</input>
                <clipto>
                    <min>-0.1</min>
                    <max>0.1</max>
                </clipto>
            </summer>

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

            <aerosurface_scale name="Rudder Control">
                <input>fcs/rudder-sum</input>
                <range>
                    <min>-1.00</min>
                    <max>1.00</max>
                </range>
                <output>fcs/rudder-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <channel name="Throttles">
         <pure_gain name="Throttle1">
            <input>fcs/throttle-cmd-norm</input>
            <gain>2</gain>
            <output>fcs/throttle-pos-norm</output>
         </pure_gain>

         <pure_gain name="Throttle2">
            <input>fcs/throttle-cmd-norm[1]</input>
            <gain>2</gain>
            <output>fcs/throttle-pos-norm[1]</output>
         </pure_gain>
        </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>24</position>
                        <time>5</time>
                    </setting>
                    <setting>
                        <position>40</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>40</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>3</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	0.0320
                              0.0000	0.0160
                              0.2600	0.0320
                              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>0.1000</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
                              0.8100	0.0000
                              1.1000	0.0240
                              1.8000	0.0110
                          </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>0.00225</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>0.0150</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>0.0250</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>
                    <abs><property>fcs/elevator-pos-norm</property></abs>
                    <value>0.0300</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 lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                        0.0000 40.0000
                             -0.2000   -0.5710	0.1000
                              0.0000	0.0000	0.6000
                              0.2500	0.7160	1.3000
                              0.3300	0.9450	0.3000
                              0.6000	0.1740	0.0000
                          </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-norm</property>
                    <value>0.0600</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>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              0.0000	-0.0500
                              0.5200	-0.1200
                          </tableData>
                      </table>
                </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>0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/CldaL">
                <description>Roll_moment_due_to_left_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-norm</property>
                    <value>0.0193</value>
                </product>
            </function>
            <function name="aero/coefficient/CldaR">
                <description>Roll_moment_due_to_right_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/right-aileron-pos-norm</property>
                    <value>-0.0193</value>
                </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-norm</property>
                    <value>0.0021</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>-0.3000</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-norm</property>
                    <value>-0.1950</value>
                </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>-18.0000</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>-9.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmflaps">
                <description>Pitch_moment_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/flap-pos-deg</property>
                    <value>-0.0025</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>0.1000</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-norm</property>
                    <value>-0.0070</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
<!--
    <output name="T38.csv" type="CSV">
        <propulsion> ON </propulsion>
    </output>
-->
</fdm_config>