<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" name="Fi-156" version="2.0" release="ALPHA" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
  <fileheader>
    <author> Ron Jensen and Aeromatic v 0.9 </author>
    <filecreationdate> 8 Jul 2007 </filecreationdate>
    <version> 0.02 </version>
    <description> Models an Fi-156. </description>
  </fileheader>
  <!--
  File:     Fi-156.xml
  Inputs:
    name:          Fi-156
    type:          light single
    max weight:    2688 lb
    wing span:     46.5 ft
    length:        32.5 ft
    wing area:     280 sq-ft
    gear type:     taildragger
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  9.60 lb/sq-ft
    CL-alpha:      5 per radian
    CL-0:          0.25
    CL-max:        1.4
  CL-max should be:
   2.49 w/o flaps
   3.68 w/ flaps
    CD-0:          0.028
    K:             0.04

-->
  <metrics>
    <wingarea unit="FT2">  280.00 </wingarea>
    <wingspan unit="FT">   46.50 </wingspan>
    <wing_incidence>          0.001 </wing_incidence>
    <chord unit="FT">    6.02 </chord>
    <htailarea unit="FT2">   44.80 </htailarea>
    <htailarm unit="FT">   16.90 </htailarm>
    <vtailarea unit="FT2">   28.00 </vtailarea>
    <vtailarm unit="FT">   16.25 </vtailarm>
    <location name="AERORP" unit="IN">
      <x> 118.20 </x>
      <y>   0.00 </y>
      <z>   36.00 </z>
    </location>
    <location name="EYEPOINT" unit="IN">
      <x>  50.70 </x>
      <y>   0.00 </y>
      <z>  45.00 </z>
    </location>
    <location name="VRP" unit="IN">
      <x>0</x>
      <y>0</y>
      <z>0</z>
    </location>
  </metrics>
  <mass_balance>
    <ixx unit="SLUG*FT2">      1974 </ixx>
    <iyy unit="SLUG*FT2">      1714 </iyy>
    <izz unit="SLUG*FT2">      3446 </izz>
    <ixy unit="SLUG*FT2">         0 </ixy>
    <ixz unit="SLUG*FT2">         0 </ixz>
    <iyz unit="SLUG*FT2">         0 </iyz>
    <emptywt unit="LBS">      2006 </emptywt>
    <location name="CG" unit="IN">
      <x> 118.20 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
    </location>
   <pointmass name="Pilot">
        <weight unit="LBS"> 170 </weight>
        <location unit="IN">
            <x> 98 </x>
            <y>  0 </y>
            <z> 1.5 </z>
        </location>
    </pointmass>
    <pointmass name="Passenger1">
        <weight unit="LBS"> 170 </weight>
        <location unit="IN">
            <x>122.0 </x>
            <y>  0.0 </y>
            <z>  1.5 </z>
        </location>
    </pointmass>
    <pointmass name="Passenger2">
        <weight unit="LBS"> 0 </weight>
        <location unit="IN">
            <x>148.0 </x>
            <y>  0.00 </y>
            <z>  1.5 </z>
        </location>
    </pointmass>
  </mass_balance>
  <ground_reactions>
    <contact type="BOGEY" name="LEFT_MAIN">
      <location unit="IN">
        <x>  73.35 </x>
        <y> -60.22 </y>
        <z> -83.975 </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">       1000.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   100.00 </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>  73.35 </x>
        <y>  60.22 </y>
        <z> -83.975 </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">       1000.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   100.00 </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> 316.90 </x>
        <y>   0.00 </y>
        <z> -18.898 </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">       1000.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   100.00 </damping_coeff>
      <max_steer unit="DEG"> -30.00 </max_steer>
      <brake_group>NONE</brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="STRUCTURE" name="LEFT_WING">
      <location unit="IN">
        <x>  110.20 </x>
        <y> -271.65 </y>
        <z>   29.00 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">       2688.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   537.60 </damping_coeff>
    </contact>
    <contact type="STRUCTURE" name="RIGHT_WING">
      <location unit="IN">
        <x>  110.20 </x>
        <y>  271.65 </y>
        <z>   29.00 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">       2688.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   537.60 </damping_coeff>
    </contact>
    <contact type="STRUCTURE" name="NOSE">
      <location unit="IN">
        <x>   0.00 </x>
        <y>   0.00 </y>
        <z>   0.00 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">       2688.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">   537.60 </damping_coeff>
    </contact>
  </ground_reactions>
  <propulsion>
    <engine file="Argus_As_10">
      <location unit="IN">
        <x>   6.00 </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="Fi-156_prop2">
      <!-- thruster file="prop_generic2f" -->
        <location unit="IN">
          <x>   6.00 </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>118.20 </x>
        <y> -60.00 </y>
        <z>  36.00 </z>
      </location>
      <capacity unit="LBS"> 132.10 </capacity>
      <contents unit="LBS"> 132.10 </contents>
    </tank>
    <tank type="FUEL" number="1">
      <location unit="IN">
        <x>118.20 </x>
        <y> 60.00 </y>
        <z> 36.00 </z>
      </location>
      <capacity unit="LBS"> 132.10 </capacity>
      <contents unit="LBS"> 132.10 </contents>
    </tank>
  </propulsion>
  <flight_control name="FCS: Fi-156">
    <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>  0.30 </max>
        </range>
        <output>fcs/elevator-pos-rad</output>
      </aerosurface_scale>
      <aerosurface_scale name="Elevator position normalized">
        <input>fcs/elevator-pos-deg</input>
        <domain>
          <min>-25</min>
          <max>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 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>
    </channel>
    <channel name="Yaw">
      <summer name="Rudder Command Sum">
        <input>fcs/rudder-cmd-norm</input>
        <input>fcs/yaw-trim-cmd-norm</input>
        <limit>
          <min> -0.35 </min>
          <max>  0.35 </max>
        </limit>
      </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 position normalized">
        <input>fcs/rudder-pos-deg</input>
        <domain>
          <min>-25</min>
          <max>25</max>
        </domain>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/rudder-pos-norm</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">
  </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 -0.750
               0.00  0.250
               0.448 2.490
               0.60  1.146
            </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> 0.0396 </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>
             -1.57    1.500
             -0.26    0.036
              0.00    0.028
              0.26    0.036
              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>0.04</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
                0.7       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> 0.00200 </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>0.028</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>
          <table>
            <independentVar lookup="row">fcs/elevator-pos-norm</independentVar>
            <tableData>
              -1.0   0.040
               0.0   0.000
               1.0   0.040
            </tableData>
          </table>
        </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>-0.1</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    0.170
              2.0    0.057
            </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     -1.100
              2.0     -0.275
            </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>-12</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>-0.01</value>
        </product>
      </function>
    </axis>
  </aerodynamics>
</fdm_config>
