Su-26M.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="su26m" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Aeromatic v 0.91 </author>
  <filecreationdate> 2010-04-08 </filecreationdate>
  <version>$Revision: 1.10 $</version>
  <description> Models a su26m2. </description>
 </fileheader>

<!--
  File:     su26m2.xml
  Inputs:
    name:          su26m
    type:          aerobatic
    max weight:    1896.3 lb
    wing span:     25.5918 ft
    length:        22.399387 ft
    wing area:     127.34995 sq-ft
    gear type:     taildragger
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  14.89 lb/sq-ft
    CL-alpha:      4.5 per radian
    CL-0:          0.17
    CL-max:        1.2
    CD-0:          0.024
    K:             0.06

-->

 <metrics>
   <wingarea  unit="FT2">  127.35 </wingarea>
   <wingspan  unit="FT" >   25.59 </wingspan>
   <wing_incidence>          0.00 </wing_incidence>
   <chord     unit="FT" >    5.14 </chord>
   <htailarea unit="FT2">   27.34 </htailarea>
   <htailarm  unit="FT" >   13.44 </htailarm>
   <vtailarea unit="FT2">   12.73 </vtailarea>
   <vtailarm  unit="FT" >   13.44 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 107.52 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  105.26 </x>
     <y>   0.00 </y>
     <z>  40.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">       322 </ixx>
   <iyy unit="SLUG*FT2">       574 </iyy>
   <izz unit="SLUG*FT2">       897 </izz>
   <emptywt unit="LBS" >      1138 </emptywt>
   <location name="CG" unit="IN">
     <x> 107.52 </x>
     <y>   0.00 </y>
     <z>  -6.72 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>  73.12 </x>
     <y> -46.07 </y>
     <z> -62.0 </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">       1896.30 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   579.26 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x>  73.12 </x>
     <y>  46.07 </y>
     <z> -62.0 </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">       1896.30 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   579.26 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="TAIL">
   <location unit="IN">
     <x> 284.60 </x>
     <y>   0.00 </y>
     <z> -22. </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">       1896.30 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  357.04 </damping_coeff>
   <max_steer unit="DEG"> -15.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

 
  <contact type="STRUCTURE" name="NOSE">
    <location unit="IN">
     <x>15.0 </x>
     <y>0</y>
     <z>-15.0</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1800.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
  </contact>

 
  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 107.52 </x>
     <y> -153.60 </y>
     <z>  -9.2 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1896.30 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   379.26 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 107.52 </x>
     <y>  153.60 </y>
     <z>  -9.2 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1896.30 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   379.26 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="Su-26M_engine">
    <location unit="IN">
      <x>  36.00 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="Su-26M_mtv">
     <location unit="IN">
       <x>  16.00 </x>
       <y>   0.00 </y>
       <z>   0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 117.52 </x>
       <y>  30.00 </y>
       <z> -9.72 </z>
     </location>
     <capacity unit="LBS"> 315.00 </capacity>
     <contents unit="LBS"> 315.00 </contents>
  </tank>


   
 </propulsion>

 <flight_control name="FCS: Su-26M">

  <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> -0.34 </min>
        <max>  0.34 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.34 </min>
        <max>  0.34 </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> -0.44 </min>
        <max>  0.44 </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> -0.44 </min>
        <max>  0.44 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.44 </min>
        <max>  0.44 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.44 </min>
        <max>  0.44 </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>
      <clipto>
        <min> -0.55 </min>
        <max>  0.55 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-sum</input>
      <range>
        <min> -0.55 </min>
        <max>  0.55 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.55 </min>
        <max>  0.55 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Flaps">
  </channel>

  <channel name="Landing Gear">
  </channel>

  <channel name="Speedbrake">
    </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>
	       -3.14    0
	       -2.94    1.1
	       -2.618	0.791
	       -2.531	0.816
	       -2.443	0.817
	       -2.356	0.797
	       -2.269	0.760
	       -2.182	0.707
	       -2.094	0.642
	       -2.007	0.565
	       -1.920	0.479
	       -1.833	0.387
	       -1.745	0.289
	       -1.658	0.187
	       -1.571	0.084
	       -1.484	-0.021
	       -1.396	-0.125
	       -1.309	-0.227
	       -1.222	-0.325
	       -1.134	-0.418
	       -1.047	-0.503
	       -0.960	-0.579
	       -0.873	-0.643
	       -0.785	-0.693
	       -0.698	-0.727
	       -0.611	-0.740
	       -0.524	-0.730
	       -0.506	-0.725
	       -0.489	-0.719
	       -0.471  -0.755
	       -0.454  -0.732
	       -0.436  -0.710
	       -0.419  -0.707
	       -0.401  -0.706
	       -0.384  -0.711
	       -0.367  -0.726
	       -0.349  -0.759
	       -0.332  -0.811
	       -0.314  -0.876
	       -0.297  -0.946
	       -0.279  -1.014
	       -0.262  -1.059
	       -0.244  -1.068
	       -0.227  -1.061
	       -0.209  -1.006
	       -0.175  -0.867
	       -0.157  -0.766
           0.00    0.0
           0.157   0.766
           0.175   0.867
	       0.209   1.006
	       0.227   1.061
	       0.244   1.068
	       0.262   1.059
	       0.279   1.014
	       0.297   0.946
	       0.314   0.876
	       0.332   0.811
	       0.349   0.759
	       0.367   0.726
	       0.384   0.711
	       0.401   0.706
	       0.419   0.707
	       0.436   0.710
	       0.454   0.732
	       0.471   0.755
	       0.489	0.719
	       0.506	0.725
	       0.524	0.730
	       0.611	0.740
	       0.698	0.727
	       0.785	0.693
	       0.873	0.643
	       0.960	0.579
	       1.047	0.503
	       1.134	0.418
	       1.222	0.325
	       1.309	0.227
	       1.396	0.125
	       1.484	0.021
	       1.571	-0.084
	       1.658	-0.187
	       1.745	-0.289
	       1.833	-0.387
	       1.920	-0.479
	       2.007	-0.565
	       2.094	-0.642
	       2.182	-0.707
	       2.269	-0.760
	       2.356	-0.797
	       2.443	-0.817
	       2.531	-0.816
	       2.618	-0.791
	       2.94     -1.1
	       3.14      0.0            
            </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> 0.00 </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>
       </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>
                  -3.14    0.024
      -2.618	0.347
      -2.531	0.449
      -2.443	0.552
      -2.356	0.654
      -2.269	0.752
      -2.182	0.843
      -2.094	0.926
      -2.007	1.000
      -1.920	1.063
      -1.833	1.115
      -1.745	1.155
      -1.658	1.183
      -1.571	1.197
      -1.484	1.199
      -1.396	1.188
      -1.309	1.164
      -1.222	1.127
      -1.134	1.077
      -1.047	1.016
      -0.960	0.943
      -0.873	0.860
      -0.785	0.768
      -0.698	0.669
      -0.611	0.565
      -0.524	0.459
      -0.506	0.438
      -0.489	0.417
      -0.471	0.339
      -0.454	0.327
      -0.436	0.312
      -0.419	0.279
      -0.401	0.254
      -0.395	0.244
      -0.390	0.238
      -0.384	0.228
      -0.378	0.221
      -0.372	0.212
      -0.367	0.202
      -0.361	0.192
      -0.355	0.182
      -0.349	0.172
      -0.343	0.162
      -0.337	0.148
      -0.332	0.140
      -0.326	0.130
      -0.320	0.120
      -0.314	0.112
      -0.308	0.102
      -0.302	0.093
      -0.297	0.084
      -0.291	0.074
      -0.285	0.067
      -0.279	0.058
      -0.273	0.050
      -0.268	0.043
      -0.262	0.037
      -0.256	0.030
      -0.250	0.025
      0.000	0.024
      0.250	0.025
      0.256	0.030
      0.262	0.037
      0.268	0.043
      0.273	0.050
      0.279	0.058
      0.285	0.067
      0.291	0.074
      0.297	0.084
      0.302	0.093
      0.308	0.102
      0.314	0.112
      0.320	0.120
      0.326	0.130
      0.332	0.140
      0.337	0.148
      0.343	0.162
      0.349	0.172
      0.355	0.182
      0.361	0.192
      0.367	0.202
      0.372	0.212
      0.378	0.221
      0.384	0.228
      0.390	0.238
      0.395	0.244
      0.401	0.254
      0.419	0.279
      0.436	0.312
      0.454	0.327
      0.471	0.339
      0.489	0.417
      0.506	0.438
      0.524	0.459
      0.611	0.565
      0.698	0.669
      0.785	0.768
      0.873	0.860
      0.960	0.943
      1.047	1.016
      1.134	1.077
      1.222	1.127
      1.309	1.164
      1.396	1.188
      1.484	1.199
      1.571	1.197
      1.658	1.183
      1.745	1.155
      1.833	1.115
      1.920	1.063
      2.007	1.000
      2.094	0.926
      2.182	0.843
      2.269	0.752
      2.356	0.654
      2.443	0.552
      2.531	0.449
      2.618	0.347
      3.14    0.024
            </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>0.06</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
                0.75      0.000
                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> 0.00 </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>0.0</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>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.04</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</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>-0.025</value>
       <!-- Asymmetric stall -->
          <table> 
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
              -15    1
              13     1
              14     10
              35     10
            </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>-0.4</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>0.08</value>
          <!-- Asymmetric stall -->
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
              -15    1
              13     1
              14     20
              35     20
            </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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.170
              2.0    0.057
            </tableData>
          </table>
       <!-- less efficient ailerons when Asymmetric stall -->
          <table> 
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
              -15    1
              13     1
              14     0.3
              35     0.3
            </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">

    <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>-0.5</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     -1.000
              2.0     -0.250
            </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>-15</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>-7</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>0.12</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>-0.003</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>