<?xml version="1.0" encoding="ISO-8859-1"?>

<!-- SE 3130 Alouette II  : BARANGER Emmanuel 03/2021
                   Update : BARANGER Emmanuel 01/2025
                   Update : BARANGER Emmanuel 07/2025
                   Update : BARANGER Emmanuel 01/2026
                   Update : BARANGER Emmanuel 04/2026

    sources               : https://www.wikiwand.com/en/A%C3%A9rospatiale_Alouette_II

    Length                :   31 ft 8 in (  9.66 m      )
    Height                :    9 ft 0 in (  2.75 m      )
    Empty weight          : 1973 lb      (   895 kg     )
    Gross weight          : 3527 lb      (  1600 kg     )
    Fuel capacity         :  580 L       (   150 US Gal )
    Powerplant            : 1 Turbomeca Artouste IIC6 turboshaft 530 hp
    Main rotor diameter   :   33 ft 6 in ( 10.20 m      )
    Maximum speed         :  185 km/h    (   100 kt     ) at sea level
    Cruise speed          :  170 km/h    (    92 kt     )
-->
<airplane mass="1973" version="YASIM_VERSION_CURRENT" mtow-lbs="3527">

   <approach           speed="10" aoa="1">
      <control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
   </approach>

   <cruise             speed="170" alt="100">
      <control-setting axis="/controls/engines/engine[0]/throttle" value="1"/>
   </cruise>

   <rotor name="main"
           x = "2.141" y = "0.0" z = "1.002"
          nx = "0.05" ny = "0"  nz = "1"
          fx = "1.00" fy = "0"  fz = "0"
          ccw                                 = "0"
          mincollective                       = "-12"   maxcollective = "12"
          mincyclicele                        = "-12"   maxcyclicele  = "12"
          mincyclicail                        = "-8"    maxcyclicail  = "8"
          diameter                            = "10.2"
          numblades                           = "3"
          weightperblade                      = "200"
          relbladecenter                      = "0.6"
          dynamic                             = "1"
          rpm                                 = "300"
          rellenflaphinge                     = "0.18"
          delta                               = "0.108" delta3        = "0"
          number-of-segments                  = "8"
          number-of-parts                     = "8"
          pitch-a                             = "10"    pitch-b       = "15"
          flapmin                             = "-15"   flapmax       = "15"
          flap0                               = "-5"    flap0factor   = "0"
          chord                               = "0.5"
          twist                               = "-7"
          notorque                            = "0"
          dragfactor                          = "0.3"
          translift-ve                        = "20"
          translift-maxfactor                 = "1.15"
          ground-effect-constant              = "0.1"
          taper                               = "1"
          rel-len-where-incidence-is-measured = "0.7"
          rel-len-blade-start                 = "0.076"
          airfoil-lift-coefficient            = "9.0"
          airfoil-drag-coefficient0           = "0.025"
          airfoil-drag-coefficient1           = "0.12"
          incidence-stall-zero-speed          = "19"
          incidence-stall-half-sonic-speed    = "14.5"
          lift-factor-stall                   = "0.18"
          stall-change-over                   = "5.5"
          drag-factor-stall                   = "2"
          cyclic-factor                       = "0.8"
          rotor-correction-factor             = "0.98"
          downwashfactor                      = "1">
          <control-input control="CYCLICELE"  axis="/controls/flight/elevator-trim"/>
          <control-input control="CYCLICAIL"  axis="/controls/flight/aileron-trim"/>
          <control-input control="CYCLICAIL"  axis="/controls/flight/aileron"              src0="-1" src1="1" dst0="-0.25" dst1=" 0.25"/>
          <control-input control="CYCLICELE"  axis="/controls/flight/elevator"             src0="-1" src1="1" dst0="-0.20" dst1=" 0.20"/>
          <control-input control="COLLECTIVE" axis="/controls/engines/engine[0]/throttle"  src0=" 0" src1="1" dst0=" 1.00" dst1=" 0.05"/>
  </rotor>

  <rotor name="tail"
          x = "-3.963" y = "-0.226" z = "0.174"
         nx = "0"     ny = "1"     nz = "0"
         fx = "1"     fy = "0"     fz = "0"
         ccw                              = "0"
         diameter                         = "1.719"
         numblades                        = "2"
         mincollective                    = "-20"   maxcollective = "14"
         chord                            = "0.259"
         weightperblade                   = "5"
         relbladecenter                   = "0.6"
         dynamic                          = "1"
         rpm                              = "3584"
         rellenflaphinge                  = "0"
         delta                            = "0.5"   delta3        = "0"
         translift                        = "0"
         pitch-a                          = "10"    pitch-b       = "15"
         airfoil-lift-coefficient         = "6.4"
         airfoil-drag-coefficient0        = "0.0035"
         airfoil-drag-coefficient1        = "0.010"
         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"
         notorque                         = "0"
         taper                            = "1"
         number-of-segments               = "5"
         number-of-parts                  = "4"
         rel-len-blade-start              = "0.4"
         rotor-correction-factor          = "0.98">
         <control-input control="COLLECTIVE" axis="/controls/flight/rudder"              src0="-1" src1="1" dst0="-0.30" dst1=" 0.40"/>
         <control-input control="COLLECTIVE" axis="/controls/engines/engine[0]/throttle" src0=" 0" src1="1" dst0=" 0.35" dst1=" 0.09"/>
  </rotor>

  <!-- Engines source            : https://www.wikiwand.com/en/articles/Turbomeca_Artouste

               name              : Turbomeca Artouste
               type              : Turboshaft
               power cruise      : 590 hp
               weight            : 154 kg ( 340 lb )
  -->
  <rotorgear max-power-engine      = "590"
             max-power-rotor-brake = "100"
             engine-prop-factor    = "0.01"
             rotorgear-friction    = "1.005"
             engine-accel-limit    = "2"
             yasimdragfactor       = "8"
             yasimliftfactor       = "12">
             <control-input control="ROTORGEARENGINEON"       axis="/controls/engines/engine[0]/magnetos"/>
             <control-input control="ROTORBRAKE"              axis="/controls/rotor/brake"        src0="0" src1="1" dst0="0" dst1="1"/>
             <control-input control="ROTORRELTARGET"          axis="/controls/rotor/reltarget"    src0="0" src1="1" dst0="0" dst1="1"/>
             <control-input control="ROTORENGINEMAXRELTORQUE" axis="/controls/rotor/maxreltorque" src0="0" src1="1" dst0="0" dst1="1"/>
  </rotorgear>

  <cockpit x="3.646" y="-0.395" z="-0.039"/>

  <!-- Fuselage left -->
  <fuselage ax=" 4.862" ay=" 0.094" az="-0.657" bx=" 4.020" by=" 0.094" bz="-0.432" width="1.440" taper="0.30" midpoint="1"/>
  <fuselage ax=" 4.136" ay=" 0.094" az="-0.446" bx=" 3.366" by=" 0.094" bz="-0.353" width="1.600" taper="0.90" midpoint="1"/>
  <fuselage ax=" 3.460" ay=" 0.094" az="-0.353" bx=" 2.852" by=" 0.094" bz="-0.353" width="1.600" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.852" ay=" 0.094" az="-0.353" bx=" 2.487" by=" 0.094" bz="-0.353" width="1.600" taper="0.70" midpoint="0"/>
  <fuselage ax=" 2.878" ay=" 0.094" az="-0.592" bx=" 0.532" by=" 0.000" bz="-0.466" width="1.120" taper="0.70" midpoint="0"/>
  <fuselage ax=" 2.487" ay=" 0.094" az="-0.353" bx=" 0.532" by=" 0.000" bz="-0.466" width="1.120" taper="0.70" midpoint="0"/>

  <!-- Fuselage right -->
  <fuselage ax=" 4.862" ay="-0.094" az="-0.657" bx=" 4.020" by="-0.094" bz="-0.432" width="1.440" taper="0.30" midpoint="1"/>
  <fuselage ax=" 4.136" ay="-0.094" az="-0.446" bx=" 3.366" by="-0.094" bz="-0.353" width="1.600" taper="0.90" midpoint="1"/>
  <fuselage ax=" 3.460" ay="-0.094" az="-0.353" bx=" 2.852" by="-0.094" bz="-0.353" width="1.600" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.852" ay="-0.094" az="-0.353" bx=" 2.487" by="-0.094" bz="-0.353" width="1.600" taper="0.70" midpoint="0"/>
  <fuselage ax=" 2.878" ay="-0.094" az="-0.592" bx=" 0.532" by=" 0.000" bz="-0.466" width="1.120" taper="0.70" midpoint="0"/>
  <fuselage ax=" 2.487" ay="-0.094" az="-0.353" bx=" 0.532" by=" 0.000" bz="-0.466" width="1.120" taper="0.70" midpoint="0"/>

  <!-- Tail -->
  <fuselage ax=" 0.532" ay=" 0.000" az="-0.466" bx="-3.900" by=" 0.000" bz=" 0.160" width="0.801" taper="0.30" midpoint="0"/>

  <hstab x="-2.830" y="0.160" z="-0.030"
         chord  = "0.282"
         length = "0.7"
         taper  = "0.94"
         sweep  = "3">
         <stall aoa="14" width="1" peak="1.5"/>
  </hstab>

  <!-- pilot -->
  <weight x="3.56" y=" 0.37" z="-0.45" mass-prop="/sim/weight[0]/weight-lb"/>
  <!-- co-pilot -->
  <weight x="3.56" y="-0.37" z="-0.45" mass-prop="/sim/weight[1]/weight-lb"/>
  <!-- right passenger -->
  <weight x="2.99" y=" 0.43" z="-0.45" mass-prop="/sim/weight[2]/weight-lb"/>
  <!-- middle passenger -->
  <weight x="2.99" y=" 0.00" z="-0.45" mass-prop="/sim/weight[3]/weight-lb"/>
  <!-- left passenger -->
  <weight x="2.99" y="-0.43" z="-0.45" mass-prop="/sim/weight[4]/weight-lb"/>
  <!-- cargo hook -->
  <weight x="2.06" y=" 0.00" z="-1.13" mass-prop="/sim/weight[5]/weight-lb"/>

  <!-- Points de Contact sur le sol -->
  <!-- LEFT -->
  <!-- Front -->
  <gear x=" 4.280" y=" 1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- Center -->
  <gear x=" 2.860" y=" 1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!--Rear -->
  <gear x=" 1.450" y=" 1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- RIGHT -->
  <!-- Front -->
  <gear x=" 4.280" y="-1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- Center -->
  <gear x=" 2.860" y="-1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- Rear -->
  <gear x=" 1.450" y="-1.220" z="-1.420"
        skid        = "1"
        compression = "0.05"
        spring      = "12"
        stiction    = "1.2">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- tail skid -->
  <gear x="-4.060" y=" 0.000" z="-0.960"
        skid        = "1"
        compression = "0.01"
        spring      = "8"
        damp        = "4"
        stiction    = "1.2"/>

  <!-- 580 l -->
  <tank x="2.0800" y="0.000" z="-0.500" capacity="800"/>


  <!-- Mass displacement center of main rotor 2.141 -->
  <!-- Engine -->
  <ballast x=" 1.100" y=" 0.000" z=" 0.300" mass="185"/>
  <!-- Fuselage -->
  <ballast x=" 3.300" y=" 0.000" z="-0.500" mass="782"/>
  <!-- Queue -->
  <ballast x="-3.000" y=" 0.000" z=" 0.000" mass="150"/>

</airplane>
