<?xml version="1.0" encoding="UTF-8"?>

<!-- Caudron G.III - 2009 BARANGER Emmanuel

     Sources      http://en.wikipedia.org/wiki/Caudron_G.3

     Envergure    : 13.40 m   (44 ft 0 in)
     Longueur     :  6.40 m   (21 ft 0 in)
     Hauteur      :  2.50 m   ( 8 ft 3 in)
     Masse        :   420 kg  (    933 lb)
     Moteur       : Le Rhone C rotary, (80 hp)
     Vitesse max  : 106 km/h  (57 kt)
-->

<airplane mass="933">

  <!-- Approach configuration -->
  <approach speed="35.6" aoa="6" fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.5"/>
    <control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise speed="55" alt="5000" fuel="0.5">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
  </cruise>

  <!-- pilot's eyepoint -->
  <cockpit x="0.872" y="0" z="0.863"/>

  <fuselage ax="3.176" ay="0" az="0.127" bx="0.104" by="0" bz="0.127" width="0.982" taper="0.8" midpoint="0.15"/>

  <!-- upper wing -->
  <wing x="1.732" y="0" z="0.959"
        chord="1.501"
        length="6.522"
        taper="1"
        incidence="5"
        camber="0.008">
        <stall aoa="24" width="4" peak="1.5"/>
        <flap1 start="0.518" end="1.0" lift="1.20" drag="1.35"/>

        <control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>

        <control-output control="FLAP1" side="left" prop="/surface-positions/left-aileron-pos-norm"/>
        <control-output  control="FLAP1" side="right" prop="/surface-positions/right-aileron-pos-norm"/>
  </wing>

  <!--lower wing -->
  <mstab x="1.859" y="0" z="-0.479"
         chord="1.223"
         length="3.930"
         incidence="5"
         taper="1"
         camber="0.008">
         <stall aoa="25" width="4" peak="1.5"/>
  </mstab>

  <!-- tailplane -->
  <hstab x="-2.823" y="0" z="-0.244"
         chord="1.158"
         length="2.292"
         taper="1">
         <stall aoa="22" width="4" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.4" drag="1.5"/>

         <control-input axis="/controls/flight/elevator" control="FLAP0"/>
         <control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>

         <control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
  </hstab>

  <!-- tail -->
  <vstab x="-2.761" y="0.620" z="-0.171"
         chord="1.063"
         length="1.4"
         taper="0.2"
         sweep="20">
         <stall aoa="20" width="4" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.3" drag="1.3"/>

         <control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/> 

         <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
  </vstab>

  <!-- tail -->
  <vstab x="-2.761" y="-0.620" z="-0.171"
         chord="1.063"
         length="1.4"
         taper="0.2"
         sweep="20">
         <stall aoa="20" width="4" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.3" drag="1.3"/>

         <control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/> 

         <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
  </vstab>

  <!-- Engines   source            : http://pagesperso-orange.fr/aircollection/lerhone.htm
                                     http://en.wikipedia.org/wiki/Le_Rh%C3%B4ne_9C

                 name              : Rhone 9C
                 type              : 9-cylinder rotary
                 power cruise      : 80 hp at 1200 rpm
                 weight            : 149 kg (330 lb)
                 Displacement      : 15,074 cc (919.9 cubic inches)
                 compression       : 5.1
                 Propeller diameter: 2.4 m (7.87 ft)
  -->
  <propeller x="2.987" y="0" z="0.141"
             mass="330"
             moment="10"
             radius="1.35"
             cruise-speed="55"
             cruise-rpm="1100"
             cruise-power="75"
             cruise-alt="0"
             takeoff-power="80"
             takeoff-rpm="1200">
             <actionpt x="3.281" y="0" z="0.231"/>
             <piston-engine eng-power="80"
                            eng-rpm="1200"
                            compression="5.1"
                            displacement="919.9">
                            <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
                            <control-input axis="/controls/engines/engine[0]/starter" control="STARTER"/>
                            <control-input axis="/controls/engines/engine[0]/magnetos" control="MAGNETOS"/>
                            <control-input axis="/controls/engines/engine[0]/mixture" control="MIXTURE"/>
             </piston-engine>
  </propeller>

  <!-- left main -->
  <gear x="2.489" y="1.583" z="-1.628"
        compression="0.02"
        dfric="0.8"
        sfric="1.0"
        damp="0.8">
        <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
  </gear>

  <!-- right main -->
  <gear x="2.489" y="-1.583" z="-1.628"
        compression="0.02"
        dfric="0.8"
        sfric="1.0"
        damp="0.8">
        <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
  </gear>

  <!-- Tail skid left-->
  <gear x="-2.648" y="1.589" z="-0.869"
        compression="0.1"
        castering="0"
        dfric="0.5"
        sfric="0.6">
  </gear>

  <!-- Tail skid right-->
  <gear x="-2.648" y="-1.589" z="-0.869"
        compression="0.1"
        castering="0"
        dfric="0.5"
        sfric="0.6">
  </gear>

  <!-- fuel -->
  <tank x="2" y="0" z="0" capacity="200"/>

  <!-- CG Theorique : x=1.565 y=0 z=0.127 -->
  <ballast x="0.42" y="0" z="-2" mass="480"/>

</airplane>
