Yak-55M.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Yak55m" 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 0.95 </author>
  <filecreationdate> 2011-09-30 </filecreationdate>
  <version>$Revision: 1.10 $</version>
  <description> Models a Yak-55M. </description>
 </fileheader>

<!--
  File:     Yak55m.xml
  Inputs:
    name:          Yak-55M
    type:          aerobatic
    max weight:    2149.875 lb
    wing span:     26.5761 ft
    length:        23.91849 ft
    wing area:     137.792 sq-ft
    gear type:     taildragger
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  15.60 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">  137.79 </wingarea>
   <wingspan  unit="FT" >   26.58 </wingspan>
   <wing_incidence>          0.00 </wing_incidence>
   <chord     unit="FT" >    5.18 </chord>
   <htailarea unit="FT2">   23.42 </htailarea>
   <htailarm  unit="FT" >   14.45 </htailarm>
   <vtailarea unit="FT2">   13.78 </vtailarea>
   <vtailarm  unit="FT" >   14.95 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 68 </x>
     <y>   0 </y>
     <z>   0 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  103 </x>
     <y>   0.00 </y>
     <z>  30.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">       516 </ixx>
   <iyy unit="SLUG*FT2">       743 </iyy>
   <izz unit="SLUG*FT2">      1126 </izz>
   <emptywt unit="LBS" >      1290 </emptywt>
   <location name="CG" unit="IN">
     <x>  68 </x>
     <y>  0 </y>
     <z>  0 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 50.0 </x>
     <y> -40.3 </y>
     <z> -64.50 </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">       2149.88 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   429.98 </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> 50.0 </x>
     <y>  40.3 </y>
     <z> -64.60 </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">       2149.88 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   429.98 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN2">
   <location unit="IN">
     <x> 50.0 </x>
     <y> -40.3 </y>
     <z> -58.0 </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">       8800 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   1500 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN2">
   <location unit="IN">
     <x> 50.0 </x>
     <y>  40.3 </y>
     <z> -58.0 </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">       8800 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   1500 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

 
 
 
 
  <contact type="BOGEY" name="TAIL">
   <location unit="IN">
     <x> 266.2 </x>
     <y>   0.00 </y>
     <z> -28.2 </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">       1498.8 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  519.90 </damping_coeff>
   <max_steer unit="DEG"> -40.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 67.8 </x>
     <y> -161.3 </y>
     <z>  -3.0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       2149.88 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   429.98 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 67.8 </x>
     <y>  161.3 </y>
     <z>  -3.0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       2149.88 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   429.98 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="NOSE">
    <location unit="IN">
     <x> 5 </x>
     <y>  0.0 </y>
     <z>  -16 </z>
    </location>
    <static_friction>  0.98 </static_friction>
    <dynamic_friction> 0.75 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1237 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   467 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="NOSE_UP">
    <location unit="IN">
     <x> 16 </x>
     <y> 0.0 </y>
     <z> 18.5 </z>
    </location>
    <static_friction>  0.98 </static_friction>
    <dynamic_friction> 0.75 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1237 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   467 </damping_coeff>
 </contact>
 
 
  <contact type="STRUCTURE" name="Kil">
    <location unit="IN">
     <x> 236 </x>
     <y>  0 </y>
     <z>  44.1 </z>
    </location>
    <static_friction>  0.98 </static_friction>
    <dynamic_friction> 0.85 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1237 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   467 </damping_coeff>
 </contact>
 
 
 
 
 </ground_reactions>

 <propulsion>

   <engine file="M-14P">
    <location unit="IN">
      <x>  20.00 </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>
	<feed>1</feed>
    <thruster file="V530">
     <location unit="IN">
       <x>  0.00 </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> 68.0 </x>
       <y>   -40.0 </y>
       <z>  0.0 </z>
     </location>
     <capacity unit="LBS"> 218.00 </capacity>
     <contents unit="LBS"> 118.00 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 68.0 </x>
       <y>  40.0 </y>
       <z>  0.0 </z>
     </location>
     <capacity unit="LBS"> 218.00 </capacity>
     <contents unit="LBS"> 118.00 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: Yak55m">

  <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>  0.35 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </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 normalization">
      <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 normalization">
      <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>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
   </summer>

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

   <aerosurface_scale name="rudder normalization">
      <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>


 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/force/Lift_alpha">
      <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>
-3.139   0.000
-2.860   0.800
-2.790   0.750
-2.354   1.000
-1.570   0.000
-0.785  -1.000
-0.523  -1.000
-0.436  -1.036
-0.349  -1.406
-0.340  -1.460
-0.331  -1.406
-0.314  -1.332
-0.296  -1.258
-0.279  -1.184
-0.262  -1.110
-0.174  -0.740
-0.087  -0.370
 0.000   0.000
 0.087   0.370
 0.174   0.740
 0.262   1.110
 0.279   1.184
 0.296   1.258
 0.314   1.332
 0.331   1.406
 0.340   1.460
 0.349   1.406
 0.436   1.036
 0.523   1.000
 0.785   1.000
 1.570   0.000
 2.354  -1.000
 2.790  -0.750
 2.860  -0.800
 3.139   0.000
            </tableData>
          </table>
      </product>
    </function>


    <function name="aero/force/Lift_elevator">
       <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>0.52</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_basic">
       <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>
-3.139      0
-2.860  0.080
-2.790  0.133
-2.354  0.446
-1.570  1.300
-0.785  0.446
-0.523  0.286
-0.436  0.233
-0.349  0.180
-0.340  0.177
-0.331  0.173
-0.314  0.145
-0.296  0.134
-0.279  0.123
-0.262  0.115
-0.174  0.068
-0.087  0.040
 0.000  0.030
 0.087  0.040
 0.174  0.068
 0.262  0.115
 0.279  0.123
 0.296  0.134
 0.314  0.145
 0.331  0.173
 0.340  0.177
 0.349  0.180
 0.436  0.233
 0.523  0.286
 0.785  0.446
 1.570  1.300
 2.354  0.446
 2.790  0.133
 2.860  0.080
 3.139      0			
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.006</value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <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
            </tableData>
          </table>
        </product>
    </function>


    <function name="aero/force/Drag_beta">
       <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/force/Drag_elevator">
       <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>0.02</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <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/moment/Roll_beta">
       <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>-0.05</value>
       <!-- Asymmetric stall -->
          <table> 
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
			  -35    10
			  -16    10
              -15    1
              15     1
              16     10
              35     10
            </tableData>
          </table>
		   
       </product>
    </function>

    <function name="aero/moment/Roll_damp">
       <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/moment/Roll_yaw">
       <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>0.075</value>
          <!-- Asymmetric stall -->
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
			  -35    20 
			  -16    20
              -15    1
              15     1
              16     20
              35     20
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <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>
            <independentVar lookup="column">propulsion/engine/propeller-rpm</independentVar>			
            <tableData>
			           0    1590  1940
             -0.080  -0.17 -0.10 -0.07
              0.000  -0.17 -0.10  0.01
			  0.057  -0.17 -0.07  0.07
              0.074  -0.07  0.00  0.12
              0.080   0.17  0.17  0.17	  
              1.000   0.16  0.16  0.16
            </tableData>
          </table>
       <!-- less efficient ailerons when Asymmetric stall -->
          <table> 
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
			  -35    0.3
			  -16    0.3
              -15    1
              15     1
              16     0.3
              35     0.3
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder">
       <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/moment/Pitch_alpha">
       <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/moment/Pitch_elevator">
       <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/moment/Pitch_damp">
       <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/moment/Pitch_alphadot">
       <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/moment/Yaw_beta">
       <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/moment/Yaw_damp">
       <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/moment/Yaw_rudder">
       <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>-0.15</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <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>