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

<!-- Dauohin d'après l'OH-1 de TAT -->
<airplane mass="5400">

  <approach speed="47" aoa="5">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
  </approach>

  <cruise speed="147" alt="0">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
  </cruise>

  <rotor name="main" 
    x="1.785" y="0.0" z="1.449" 
    nx="0.043" ny="0" nz="0.999" 
    fx="0.99" fy="0" fz="-0.043" 
    ccw="1" phi0="45"
    maxcollective="15.0" mincollective="0.2"
    mincyclicail="-6" maxcyclicail="4"
    mincyclicele="-4.7" maxcyclicele="14.5"
    diameter="11.6" numblades="4" weightperblade="60" relbladecenter="0.5"
    dynamic="1" rpm="365" rellenflaphinge="0.2" delta3="0.0"
    delta=".25"
    pitch-a="10"
    pitch-b="15"
    flapmin="-13.0"
    flapmax="13.0"
    flap0="-2.0"
    flap0factor="0"
    notorque="0"
    dragfactor="0.30"
    translift-ve="20"
    translift-maxfactor="1.3"
    ground-effect-constant="0.1"
    twist="-8.5"
    taper="1"
    chord="0.38"
    number-of-segments="8"
    number-of-parts="8"
    rel-len-where-incidence-is-measured="0.7"
    rel-len-blade-start="0.076"
    airfoil-lift-coefficient="3.55"
    airfoil-drag-coefficient0="0.0150"
    airfoil-drag-coefficient1="0.25"
    incidence-stall-zero-speed="13"
    incidence-stall-half-sonic-speed="12.5"
    lift-factor-stall="0.18"
    stall-change-over="5.5"
    drag-factor-stall="2.0"
    cyclic-factor="1.0"
    rotor-correction-factor="0.9">
    <control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="true"/>
    <control-input axis="/controls/flight/fcs/roll" control="CYCLICAIL" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
    <control-input axis="/controls/flight/elevator-trim" control="CYCLICELE" split="true"/>
    <control-input axis="/controls/flight/fcs/pitch" control="CYCLICELE" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
    <control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE" src0="0.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
  </rotor>


  <rotor name="tail" 
    x="-13.55" y="-0.431" z="2.145" 
    nx="0.07" ny="-1" nz="-0.05"
    fx="1" fy="0" fz="0"
    ccw="1"
    maxcollective="15" mincollective="-9.5"
    diameter="1" numblades="8" weightperblade="1" relbladecenter="0.7"
    dynamic="1" rpm="3584" rellenflaphinge="0.0" delta3="0" translift="0" delta="0.5"
    pitch-a="10"
    pitch-b="15"
    airfoil-lift-coefficient="6.4"
    airfoil-drag-coefficient0="0.0035"
    airfoil-drag-coefficient1="0.10"
    notorque="0"
    taper="1"
    chord="0.205"
    number-of-segments="5"
    number-of-parts="4"
    rel-len-blade-start="0.4"
    incidence-stall-zero-speed="16"
    incidence-stall-half-sonic-speed="18"
    lift-factor-stall="0.18"
    stall-change-over="5.5"
    drag-factor-stall="8"
    rotor-correction-factor="0.7">
    <control-input axis="/controls/flight/fcs/yaw" control="COLLECTIVE" invert="true" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
    <control-input axis="/controls/flight/fcs/tail-rotor/throttle" control="COLLECTIVE" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
  </rotor>

  <rotorgear
    max-power-engine="1185"
    max-power-rotor-brake="100"
    rotorgear-friction="1.4"
    engine-prop-factor="0.005"
    engine-accel-limit="2.96"
    yasimdragfactor="12.5"
    yasimliftfactor="170">
    <control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
    <control-input axis="/controls/rotor/brake" control="ROTORBRAKE" src0="0.0" src1="1.0" dst0="0.0" dst1="1.0"/>
  </rotorgear>

  <cockpit x="4.143" y="-0.344" z="-0.218"/>

  <!-- Fuse -->
  <fuselage ax="8.010" ay="0" az="-0.534" bx="-4.476" by="0" bz="-0.534" width="2" taper="0.5" midpoint="0.35"/>

  <vstab x="-3.938" y="1.512" z="-1.218"
         taper=".5" 
         length="2.5" 
         chord="1.38" 
         sweep="45" 
         incidence="5">
         <stall aoa="16" width="4" peak="1.5"/>
  </vstab>

  <vstab x="-3.938" y="-1.512" z="-1.218"
         taper=".5" 
         length="2.5" 
         chord="1.38" 
         sweep="45" 
         incidence="5">
         <stall aoa="16" width="4" peak="1.5"/>
  </vstab>

  <hstab x="-3.938" y="0" z="-0.364"
         taper="1.0"
         effectiveness="0.5" 
         length="1.27" 
         chord="0.52" 
         sweep="0">
         <stall aoa="0" width="0" peak="1.5"/>
  </hstab>

  <!-- Avant -->
  <gear x="4.811" y="0" z="-1.844" 
        skid="1" 
        compression="0.30"
        spring="1.0" 
        damp="0.2" 
        sfric="0.5" 
        dfric="0.4">
        <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
        <control-speed control="EXTEND" transition-time="7"/>
        <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
  </gear>

  <!-- Arrière gauche -->
  <gear x="0.857" y="1.001" z="-1.844" 
        skid="1" 
        compression="0.30"
        spring="1.0" 
        damp="0.2" 
        sfric="0.5" 
        dfric="0.4">
        <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
        <control-speed control="EXTEND" transition-time="7"/>
        <control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>
  </gear>

  <!-- Arrière droit -->
  <gear x="0.857" y="-1.001" z="-1.844" 
        skid="1" 
        compression="0.30"
        spring="1.0" 
        damp="0.2" 
        sfric="0.5" 
        dfric="0.4">
        <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
        <control-speed control="EXTEND" transition-time="7"/>
        <control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>
  </gear>

  <tank x="1.39" y="0" z="-.31" capacity="75"/>
  <tank x="1.47" y="0" z="-.31" capacity="75"/>
  <tank x="1.8" y="0" z="0" capacity="75"/>
  <!-- work around bug in native-fdm.cxx:184 -->
  <tank x="0" y="0" z="0" capacity="0"/>
  <ballast x="3.0" y="+0.0" z="-0.5" mass="100"/>
  <ballast x="0.78" y=" 1.1" z="1.1" mass="350"/>
  <ballast x="0.78" y="-1.1" z="1.1" mass="150"/>

  <!-- pilot -->
  <weight x="1.76" y="0" z="1.36" mass-prop="/sim/weight[1]/weight-lb"/>
  <!-- co-pilot -->
  <weight x="1.61" y="0"  z="1.88" mass-prop="/sim/weight[2]/weight-lb"/>

  <!-- hitch -->
  <hitch name="aerotow" x="-1.320" y="0" z="-0.762"  force-is-calculated-by-other="1">
    <tow length="60" weight-per-meter="0.035" elastic-constant="9000" break-force="10000" mp-auto-connect-period="1.0"/>
    <winch max-tow-length="1000" min-tow-length="60" initial-tow-length="60"/>
    <control-input axis="/controls/aerotow/find-aircraft" control="FINDAITOW"/>
  </hitch>

</airplane>



