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

    <fileheader>
        <author> Tatsuhiro Nishioka </author>
        <filecreationdate> 2007-12-15 </filecreationdate>
        <version> $Revision$ </version>
        <description> Kawasaki Heavy Industries T-4 "Blue Impulse" </description>
        <reference refID="1" author="JASDF" title="T-4: JASDF official site[JASDF]" date="unknown"/>
        <reference refID="2" author="greg goebel" title="The Mitsubishi T-2 / F-1 and Kawasaki T-4" URL="http://www.faqs.org/docs/air/avt2f1.html" date="Sep/01/2003"/>
        <reference refID="3" author="Syutendouji" title="T-4 Tanjo (Birth of T-4)" URL="http://www16.plala.or.jp/amber-devil/dolphin03.htm" date="n/a"/>
        <reference refID="4" author="" title="The Engine for T-4: F3-IHI-30" URL="http://rightwing.sakura.ne.jp/equipment/jasdf/engine/f3ihi30/f3ihi30.html" date="n/a"/>
    </fileheader>

<!--
Calculation note (unit = meter) measured on an ac3d model
MAC is calculated with http://www.geistware.com/rcmodeling/cg_super_calc.htm
Main Wing:
 Root chord	3.17
 Tip chord	1.10
 Sweep Distance	3.05
 Half span	4.95
 Aerodynamic center: 
		25% MAC; 1.90 from Root Leading Edge
 MAC		2.32
 Wing area	21.0
 point at leading edge of the root wing: x = -1.34 (on an ac3d model)
 Neutral point from Root Leadig Edge: 2.4)
  

HTail:
 Root chord	1.74
 Tip  chord	0.86
 Sweep Distance	1.38
 Half Span	1.17
 MAC		1.35
 Wing area	6.00
Distance between Wing and HTail root leading edges
		5.79
 HTail arm	4.90

VTail:
 Root chord	2.33
 Tip chord	0.70
 Sweep Distance	2.53
 Half Span	2.90
 MAC		1.66
Distance between Wing and VTail root leading edges
		4.16
 VTail arm	3.67

Aerodynamic reference point:	
Neutral Point %MAC:		46.6% (2.4m from root leading edge; (1.14, 0, -0.32))

-->

    <metrics>
        <wingarea  unit="FT2"> 226.05 </wingarea>
        <wingspan  unit="FT">   32.61 </wingspan>   <!-- from ref[2] -->
        <wing_incidence>         2.00 </wing_incidence>
        <!-- MAC -->
        <chord     unit="FT">    7.87 </chord>
	<htailarea unit="FT2">   61.40 </htailarea>
	<htailarm  unit="FT">    15.84 </htailarm>
	<vtailarea unit="FT2">   52.50 </vtailarea>
	<vtailarm  unit="FT">    12.04 </vtailarm>

        <!-- x:tail=positive; y:right=positive; z:up=positive -->

        <location name="AERORP" unit="IN"> <!-- 25% MAC @ 2.14m from the center line -->
            <x> 20.47 </x>
            <y> 0.00 </y>
            <z> 12.60 </z> 
        </location>
        <location name="EYEPOINT" unit="IN"> <!-- pilot's eye point -->
            <x> -106.30 </x>
            <y>    0.00 </y>
            <z>   39.37 </z>
        </location>
        <location name="VRP" unit="IN"> <!-- the nose tip of the airplane -->
            <x> -232.28 </x>
            <y>    0.00 </y>
            <z>   -3.14 </z>
        </location>
    </metrics>

 <mass_balance>
   <!-- by aeromatic; should be calculated properly -->
   <ixx unit="SLUG*FT2">      5888 </ixx>
   <iyy unit="SLUG*FT2">     13801 </iyy>
   <izz unit="SLUG*FT2">     16770 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">      -800 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >      8536 </emptywt>
   <location name="CG" unit="IN">
     <x> 25.50 </x>
     <y>  0.00 </y>
     <z>  7.48 </z>
   </location>

   <pointmass name="Pilot">
      <weight unit="LBS"> 180 </weight>
      <location name="POINTMASS" unit="IN">
         <x> -108.6 </x>
         <y> 0 </y>
         <z> 12 </z>
      </location>
   </pointmass>
   <pointmass name="Trainer">
      <weight unit="LBS"> 180 </weight>
      <location name="POINTMASS" unit="IN">
         <x> -56.29 </x>
         <y> 0 </y>
         <z> 35.43 </z>
      </location>
   </pointmass>
 </mass_balance>

 <ground_reactions>
  <!-- positions are measured using ac3d, but coefs are not calculated yet -->
  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> -170.87 </x> <!-- -4.34m -->
     <y>    0.00 </y>
     <z>  -57.09 </z>
<!--
     <z>  -57.09 </z>
     <z>  -62.18 </z>
-->
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       4960.20 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  1653.40 </damping_coeff>
   <max_steer unit="DEG"> 5.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>  33.46 </x> 
     <y> -62.59 </y>
     <z> -59.09 </z>
<!--
     <z> -66.18 </z>
-->
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      16534.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  3306.80 </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>  33.46 </x> 
     <y>  62.59 </y>
     <z> -59.09 </z>
<!--
     <z> -66.18 </z>
-->
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      16534.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  3306.80 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WT">
    <location unit="IN">
     <x>  33.46 </x>
     <y> -14.56 </y>
     <z> -26.77 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      16534.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  3306.80 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WT">
    <location unit="IN">
     <x>  33.46 </x>
     <y>  14.56 </y>
     <z> -26.77 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      16534.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  3306.80 </damping_coeff>
 </contact>

 </ground_reactions>

 <!-- everything below is by aeromatic -->
 <propulsion>
   <engine file="F3-IHI-30">
    <location unit="IN">
      <x> 98.42 </x>
<!--
      <x>  0.00 </x> 
-->
      <y> -27.16 </y>
      <z>  -9.05 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN"> <!-- 3.89m, 0.46m, -0.25m -->
       <x> 153.15 </x>
       <y> -18.11 </y>
       <z>  -9.84 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="F3-IHI-30">
    <location unit="IN">
      <x> 98.42 </x>
      <y>  27.16 </y>
      <z>  -9.05 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 153.15 </x>
       <y>  18.11 </y>
       <z>  -9.84 </z>
<!--
       <x> 146.85 </x>
       <y>  27.16 </y>
       <z> -6.69 </z>
-->
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <!-- pos need to be replaced -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> -57.55 </x>
       <y> -10.00 </y>
       <z> -11.81 </z>
     </location>
     <capacity unit="LBS"> 2000.00 </capacity>
     <contents unit="LBS"> 1820.00 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> -57.55 </x>
       <y>  10.00 </y>
       <z> -11.81 </z>
     </location>
     <capacity unit="LBS"> 2000.00 </capacity>
     <contents unit="LBS"> 1820.00 </contents>
  </tank>
 </propulsion>

 <flight_control name="FCS: T-4">

  <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> -0.2582 </min>
        <max>  0.2582</max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Elevator position normalized">
    <input>fcs/elevator-pos-deg</input>
    <domain>
     <min>-15</min>
     <max>15</max>
    </domain>
    <range>
     <min>-1</min>
     <max>1</max>
    </range>
    <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>
  </channel>

  <channel name="Roll">
<!--
   <pure_gain name="roll rate norm">
    <input>velocities/p-aero-rad_sec</input>
    <gain>0.31831</gain>
   </pure_gain>

   <summer name="roll trim error">
    <input>fcs/aileron-cmd-norm</input>
   </summer>

   <pure_gain name="roll rate p">
    <input>fcs/roll-trim-error</input>
    <gain>3.0</gain>
   </pure_gain>
 
   <integrator name="roll rate i">
    <input>fcs/roll-trim-error</input>
    <c1>0.05</c1>
   </integrator> 

   <lead_lag_filter name="roll rate d">
    <input>fcs/roll-trim-error</input>
    <c1>-0.00125</c1>
    <c2>0.0</c2>
    <c3>0.0</c3>
    <c4>1.0</c4>
   </lead_lag_filter>

   <summer name="roll rate command">
    <input>fcs/roll-rate-p</input>
    <input>fcs/roll-rate-i</input>
    <input>fcs/roll-rate-d</input>
    <clipto>
     <min>-1</min>
     <max> 1</max>
    </clipto>
    <output>fcs/left-aileron-pos-norm</output>
   </summer>

   <summer name="roll rate command">
    <input>fcs/roll-rate-p</input>
    <input>fcs/roll-rate-i</input>
    <input>fcs/roll-rate-d</input>
    <clipto>
     <min>-1</min>
     <max> 1</max>
    </clipto>
    <output>fcs/right-aileron-pos-norm</output>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
    <input>fcs/roll-rate-command</input>
    <range>
     <min>-0.375</min>
     <max>0.375</max>
    </range>
    <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
    <input>-fcs/roll-rate-command</input>
    <range>
     <min>-0.375</min>
     <max>0.375</max>
    </range>
    <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>
-->

   <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 position normalized">
    <input>fcs/left-aileron-pos-deg</input>
    <domain>
     <min>-20</min>
     <max>15</max>
    </domain>
    <range>
     <min>-0.75</min>
     <max>1</max>
    </range>
    <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron position normalized">
    <input>fcs/right-aileron-pos-deg</input>
    <domain>
     <min>-20</min>
     <max>15</max>
    </domain>
    <range>
     <min>-0.75</min>
     <max>1</max>
    </range>
    <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>

<!--
   <summer name="Roll Trim Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>
-->
  </channel>

  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <limit>
        <min> -0.25 </min>
        <max>  0.25 </max>
      </limit>
   </summer>

   <aerosurface_scale name="Rudder Control">
    <input>fcs/rudder-command-sum</input>
    <range>
     <min> -0.25 </min>
     <max>  0.25 </max>
    </range>
    <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Rudder position normalized">
    <input>fcs/rudder-pos-deg</input>
    <domain>
     <min>-15</min>
     <max>15</max>
    </domain>
    <range>
     <min>-1</min>
     <max>1</max>
    </range>
    <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

   <scheduled_gain name="Yaw Damper Rate">
      <input>velocities/r-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     2.00
         </tableData>
      </table>
   </scheduled_gain>

   <scheduled_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30     0.00
           60     0.00
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Yaw Damper Sum">
      <input>fcs/yaw-damper-beta</input>
      <input>fcs/yaw-damper-rate</input>
      <limit>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </limit>
   </summer>

   <scheduled_gain name="Yaw Damper Final">
      <input>fcs/yaw-damper-sum</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30         0.0
           31         1.0
        </tableData>
      </table>
   </scheduled_gain>

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

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>
  </channel>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position> 15 </position>
          <time>      4 </time>
       </setting>
       <setting>
          <position> 30 </position>
          <time>      3 </time>
       </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="Flap position normalized">
    <input>fcs/flap-pos-deg</input>
    <domain>
     <min>0</min>
     <max>30</max>
    </domain>
    <range>
     <min>0</min>
     <max>1</max>
    </range>
    <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>
  </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>

   <scheduled_gain name="Scheduled Steer Pos Deg">
     <input>fcs/steer-cmd-norm</input>
     <table>
       <independentVar>velocities/vg-fps</independentVar>
       <tableData>
         10.0        80.0
         50.0        15.0
         150.0       2.0
       </tableData>
     </table>
     <output>fcs/steer-pos-deg</output>
   </scheduled_gain>

  </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="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>
            <tableData>
              -0.20 -0.640
               0.00  0.080
               0.26  1.000
               0.60  0.448
            </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> 0.01167 </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</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> <!-- was 0.2 -->
       </product>
    </function>

  </axis>

  <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 lookup="row">aero/alpha-rad</independentVar>
<!--
            <tableData>
             -1.57    1.200
             -0.26    0.028
              0.00    0.018
              0.26    0.028
              1.57    1.200
            </tableData>
-->
            <tableData>
             -1.57    1.500
             -0.26    0.031
              0.00    0.024
              0.26    0.031
              1.57    1.500
            </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>0.09</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 lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.81      0.000
                0.90      0.007
                1.10      0.023
                1.80      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> 0.00250 </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>0.02</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>0.024</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 lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57    1.230
              -0.26    0.050
               0.00    0.000
               0.26    0.050
               1.57    1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-norm</property>
           <value>0.02</value> <!-- was 0.04 -->
       </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</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clb">
       <description>Roll_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>-0.059</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.180
              2.0    0.050
            </tableData>
<!--
            <tableData>
              0.0    0.120
              2.0    0.040
            </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>0.02</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>-0.3</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.900 <!-- was -0.800 -->
              2.0     -0.200
            </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>-18</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>-10</value> <!-- was -9 -->
       </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>0.12</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>-0.10</value> <!-- was -0.10 -->
       </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>

</fdm_config>

