c170b.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="c170b" 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 0.96 </author>
  <filecreationdate>2022-10-21</filecreationdate>
  <version>$Revision: 1.20 $</version>
  <description> Models a c170b. </description>
 </fileheader>

<!--
  File:     c170b.xml
  Inputs:
    name:          c170b
    type:          light single
    max weight:    2200.0 lb
    wing span:     36.0 ft
    length:        25.0 ft
    wing area:     6 sq-ft
    gear type:     taildragger
    castering:     
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  366.67 lb/sq-ft
    payload:       654.4 lbs
    CL-alpha:      5 per radian
    CL-0:          0.25
    CL-max:        1.4
    CD-0:          0.028
    K:             0.04

-->

 <metrics>
   <wingarea  unit="FT2">  174.00 </wingarea>
   <wingspan  unit="FT" >   36.00 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >    5.33 </chord>
   <htailarea unit="FT2">    21.96 </htailarea>
   <htailarm  unit="FT" >   15.50 </htailarm>
   <vtailarea unit="FT2">    16.60 </vtailarea>
   <vtailarm  unit="FT" >   0.50 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 113.10 </x>
     <y>   0.00 </y>
     <z>   -8.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  110.00 </x>
     <y>   0.00 </y>
     <z>  -6.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">       948 </ixx>
   <iyy unit="SLUG*FT2">       1055 </iyy>
   <izz unit="SLUG*FT2">      1600 </izz>
   <emptywt unit="LBS" >      1205 </emptywt>
   <location name="CG" unit="IN">
     <x> 116.00 </x>
     <y>   0.00 </y>
     <z>  -9.0 </z>
   </location>

        <pointmass name="Pilot">
            <weight unit="LBS"> 180 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 103 </x>
                <y> -10.20 </y>
                <z> -6.30 </z>
            </location>
        </pointmass>

        <pointmass name="Co-Pilot">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 103 </x>
                <y> 10.20 </y>
                <z> -6.30 </z>
            </location>
        </pointmass>

        <pointmass name="Left Passenger">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 135 </x>
                <y> -10.20 </y>
                <z> -9.16 </z>
            </location>
        </pointmass>

        <pointmass name="Right Passenger">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 135 </x>
                <y> 10.20 </y>
                <z> -9.16 </z>
            </location>
        </pointmass>

        <pointmass name="Baggage">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 152 </x>
                <y>  0 </y>
                <z> -14 </z>
            </location>
        </pointmass> 
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 79.52 </x>
     <y> -45.27 </y>
     <z> -62.40 </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">       2000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  160.00 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC">320</damping_coeff_rebound>
   <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> 79.52 </x>
     <y>  45.27 </y>
     <z> -62.40 </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">       2000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  160.00 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC">320</damping_coeff_rebound>
   <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> 328.34 </x>
     <y>   0.00 </y>
     <z> -24.86 </z>
   </location>
   <static_friction>  0.52 </static_friction>
   <dynamic_friction> 0.40 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       800.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  90.00 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC">180</damping_coeff_rebound>
   <max_steer unit="DEG"> 45.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 144.00 </x>
     <y> -18.00 </y>
     <z>  -7.50 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       2200.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  2200.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 144.00 </x>
     <y>  18.00 </y>
     <z>  -7.50 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       2200.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  2200.00 </damping_coeff>
  </contact>

 </ground_reactions>

	<propulsion>

		<engine file="O-300-A">

			<feed>0</feed>
    
			<thruster file="HZ-C2YR-1BF">
				<sense> 1 </sense>
				<location unit="IN">
					<x>  13.00 </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>   36.00 </x>
				<y>    0.0 </y>
				<z>    0.0 </z>
			</location>
			<capacity unit="LBS">  0.10 </capacity>
			<contents unit="LBS">  0.00 </contents>
			<type>AVGAS</type>  
			<priority>1</priority>
		</tank>

		<tank type="FUEL" number="1">
			<location unit="IN">
				<x> 114.56 </x>
				<y> -39.37 </y>
				<z>  21.50 </z>
			</location>
			<capacity unit="LBS"> 126.50 </capacity>
			<contents unit="LBS">  81.40 </contents>
			<type>AVGAS</type>  
		</tank>

		<tank type="FUEL" number="2">
			<location unit="IN">
				<x> 114.56 </x>
				<y>  39.37 </y>
				<z>  21.50 </z>
			</location>
			<capacity unit="LBS"> 126.50 </capacity>
			<contents unit="LBS">  81.40 </contents>
			<type>AVGAS</type>  
		</tank>

	</propulsion>

	<system file="fuel"/>

 <flight_control name="FCS: c170b">

  <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> -0.3 </min>
        <max>  0.3 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.3 </min>
        <max>  0.3 </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> -0.25 </min>
        <max>  0.25 </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> -0.25 </min>
        <max>  0.25 </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> -0.25 </min>
        <max>  0.25 </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> -0.25 </min>
        <max>  0.25 </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> -1 </min>
        <max>  1 </max>
      </clipto>
   </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 normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.25 </min>
        <max>  0.25 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

		<!--	Implement spring simulation based on https://forum.flightgear.org/viewtopic.php?f=4&t=39615, thanks to OO-ZVY!	-->
		<fcs_function>
			<function>
				<product>
					<property>fcs/rudder-pos-norm</property>
					<table>
						<independentVar lookup="row">/velocities/groundspeed-kt</independentVar>
						<tableData>
							0	1
							5	1
							10	0.3
						</tableData>
					</table>
				</product>
			</function>
			<output>fcs/steer-cmd-norm</output>
		</fcs_function>

  </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>10</position>
                        <time>1.0</time>
                    </setting>
                    <setting>
                        <position>20</position>
                        <time>1.0</time>
                    </setting>
                    <setting>
                        <position>30</position>
                        <time>1.2</time>
                    </setting>
                    <setting>
                        <position>40</position>
                        <time>1.5</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">
  </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>
              -0.20 -0.750
               0.00  0.250
               0.23  1.400
               0.60  0.710
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/force/Lift_flap">
       <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> 0.00899 </value>
       </product>
    </function>

    <function name="aero/force/Lift_speedbrake">
       <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/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>0.15</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>
	   <value>0.029</value>
       </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>0.054</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
                0.7      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/force/Drag_flap">
       <description>Drag due to flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.00300 </value>
         </product>
    </function>

    <function name="aero/force/Drag_speedbrake">
       <description>Drag due to speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.048</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    1.230
              -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>0.05</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>-0.025</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>-0.6</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>0.35</value>
       </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>
          <value>0.27</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>0.03</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     -1.100
              2.0     -0.275
            </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>-19</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>-10</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>0.32</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>-0.35</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>-0.3</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>-0.04</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

 <external_reactions>
 </external_reactions>

</fdm_config>