<?xml version="1.0"?>

<!-- DaSH Human-Powered Airplane    -->
<!-- Copyright 2014 Marshall Gusman -->

<fdm_config name="dash-fdm" 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>2014-08-14</filecreationdate>
  <version>$Revision: 1.15 $</version>
  <description> Models a dash. </description>
 </fileheader>

<!--
  File:     dash-fdm.xml
  Inputs:
    name:          dash
    type:          HPA
    max weight:    275.625 lb
    wing span:     109.2573 ft
    length:        29.529 ft
    wing area:     387.151057404 sq-ft
    gear type:     tricycle
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  0.71 lb/sq-ft
    payload:       173.8 lbs
    CL-alpha:      5.5 per radian
    CL-0:          0.25
    CL-max:        1.4
    CD-0:          0.012
    K:             0.023

-->

 <metrics>
   <wingarea  unit="M2">  35.964 </wingarea>
   <wingspan  unit="M" >  33.30  </wingspan>
   <wing_incidence>        5.00  </wing_incidence>
   <chord     unit="M" >   0.967 </chord>
<!-- For turbulence model -->
   <htailarea unit="M2">   2.25 </htailarea>
   <htailarm  unit="M" >   5.25 </htailarm>
   <vtailarea unit="M2">   2.55 </vtailarea>
   <vtailarm  unit="M" >   6.00 </vtailarm>
<!-- end -->
   <location name="AERORP" unit="M">
     <x>   0.790 </x>
     <y>   0.00  </y>
     <z>   0.778 </z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x>   1.00 </x>
     <y>   0.00 </y>
     <z>   1.00 </z>
   </location>
   <location name="VRP" unit="M">
     <x>1</x>
     <y>0</y>
     <z>1</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="KG*M2">      5218 </ixx>
   <iyy unit="KG*M2">       170 </iyy>
   <izz unit="KG*M2">      2503 </izz>
   <emptywt unit="KG" >      40.89 </emptywt>
   <location name="CG" unit="M">
     <x>   0.790 </x>
     <y>   0.00  </y>
     <z>   0.778 </z>
   </location>
   <pointmass name="Pilot Weight">
    <description> Pilot Weight</description>
    <weight unit="LBS">    155.0 </weight>
    <location name="POINTMASS" unit="M">
      <x>   0.790 </x>
      <y>   0.00  </y>
      <z>   0.778 </z>
    </location>
  </pointmass> 
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
    <location unit="M">
     <x> -0.72 </x>
     <y>  0.00 </y>
     <z>  0.05 </z>
   </location>
   <static_friction>  0.800 </static_friction>
   <dynamic_friction> 0.500 </dynamic_friction>
   <rolling_friction> 0.020 </rolling_friction>
   <spring_coeff  unit="N/M">      5000.00 </spring_coeff>
   <damping_coeff unit="N/M/SEC">   500.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>
  
  <contact type="BOGEY" name="MAIN">
    <location unit="M">
      <x>  1.05 </x>
      <y>  0.00 </y>
      <z> -0.08 </z>
    </location>
    <static_friction>  0.800 </static_friction>
    <dynamic_friction> 0.500 </dynamic_friction>
    <rolling_friction> 0.020 </rolling_friction>
    <spring_coeff  unit="N/M">      5000.00 </spring_coeff>
    <damping_coeff unit="N/M/SEC">   500.00 </damping_coeff>
    <max_steer unit="DEG">0</max_steer>
    <brake_group>LEFT</brake_group>
	<retractable>0</retractable>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="M">
     <x>   0.50 </x>
     <y> -16.65 </y>
     <z>   0.80 </z>
   </location>
   <static_friction>  0.20 </static_friction>
   <dynamic_friction> 0.20 </dynamic_friction>
   <spring_coeff  unit="N/M">      100.00 </spring_coeff>
   <damping_coeff unit="N/M/SEC">  500.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="M">
     <x>   0.50 </x>
     <y>  16.65 </y>
     <z>   0.80 </z>
   </location>
   <static_friction>  0.20 </static_friction>
   <dynamic_friction> 0.20 </dynamic_friction>
   <spring_coeff  unit="N/M">      100.00 </spring_coeff>
   <damping_coeff unit="N/M/SEC">  500.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="TAIL">
    <location unit="M">
     <x>   7.40 </x>
     <y>   0.00 </y>
     <z>   0.74 </z>
   </location>
   <static_friction>  0.20 </static_friction>
   <dynamic_friction> 0.20 </dynamic_friction>
   <spring_coeff  unit="N/M">      100.00 </spring_coeff>
   <damping_coeff unit="N/M/SEC">  500.00 </damping_coeff>
  </contact>

 </ground_reactions>

 <propulsion>

   <engine file="dash-engine">
    <location unit="M">
      <x>   0.790 </x>
      <y>   0.00  </y>
      <z>   0.778 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="dash-prop">
     <sense> 1 </sense>
     <location unit="M">
       <x>  -0.747</x>
       <y>   0.00 </y>
       <z>   2.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

 </propulsion>

 <flight_control name="FCS: dash">

  <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="Yaw">

   <summer name="Rudder Command Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </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>

  <channel name="Landing Gear">
  </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-deg</independentVar>
            <tableData>
              -10.0   0.0
                0.0   1.06343
                1.29  1.2
                5.0   1.58
               10.0   1.58
               20.0   1.0
            </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>0.3199</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>
             -1.57    1.5
             -0.184   0.0651
              0.00    0.02226
              0.0227  0.02609
              0.0729  0.03668
              0.35    0.5
              1.57    1.5
            </tableData>
          </table>
       </product>
    </function>

<!-- Induced drag already included in AVL
    <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>0.023</value>
         </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    1.5
              -0.17    0.00792
               0.00    0.000
               0.17    0.00792
               1.57    1.5
            </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>
           <property>fcs/elevator-pos-rad</property>
           <value>-0.1679</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>-0.428076</value>
       </product>
    </function>

    <function name="aero/force/Side_roll">
       <description>Side force due to roll</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/bi2vel</property>
           <property>velocities/p-aero-rad_sec</property>
           <value>-0.272372</value>
       </product>
    </function>

    <function name="aero/force/Side_yaw">
       <description>Side force due to yaw</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>0.225611</value>
       </product>
    </function>

    <function name="aero/moment/Side_rudder">
       <description>Side force due to rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.2427</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>-0.170813</value>
       </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>-0.804920</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>0.341478</value>
       </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>-0.0100</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>-2.806622</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>
          <value>-1.594</value>
       </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>-18.561228</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>-0</value>  <!-- WAS:-12 -->
       </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>0.014540</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>-0.028528</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_roll">
       <description>Yaw 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>-0.130003</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>0.0432</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

  <external_reactions>
  </external_reactions>

  <system file="dash-power-curves"/>
  <system file="dash-wingflex"/>

</fdm_config>
