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

<!-- Mil Mi 2 Hoplite   : 05/2024 - Emmanuel BARANGER
                 Update : 03/2026 - Emmanuel BARANGER
                 Update : 05/2026 - Emmanuel BARANGER

     Sources : https://www.wikiwand.com/en/Mil_Mi-2

     Length              :   11.4 m    (   37 ft 5 in )
     Rotor diameter      :
     Height              :   3.75 m    (   12 ft 4 in )
     Empty weigth        :   2372 kg   ( 5229 lb      )
     Max takeoff weight  :   3700 kg   ( 8157 lb      )
     Main rotor diameter :   14.5 m    (   47 ft 7 in )
     Powerplant          : 2 Klimov GTD-350P turboshaft engines ( 400 hp each )
     Fuel capacity       :    600 L    (  160 US gal  ) standard internal fuel
                           with provision for additional 423 L ( 112 US gal) in auxiliary tanks
     Cruise speed        :    194 km/h ( 110 kn       )
     Maximum speed       :    210 km/h ( 110 kn       )
-->
<airplane mass="5229" version="YASIM_VERSION_CURRENT" mtow-lbs="8157">

  <approach          speed="30">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
    <control-setting axis="/controls/engines/engine[1]/throttle" value="0.3"/>
  </approach>

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

  <rotor name="main"
         x                                   = "2.866"  y = "0"  z = "1.753"
         nx                                  = "0.09"  ny = "0" nz = "1"
         fx                                  = "1"     fy = "0" fz = "0"
         ccw                                 = "0"
         mincollective                       = "-12"   maxcollective = "12"
         mincyclicele                        = "-12"    maxcyclicele = "12"
         mincyclicail                        = "-8"     maxcyclicail = "8"
         diameter                            = "14.5"
         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"
         chord                               = "0.5"
         twist                               = "-10"
         pitch-a                             = "10"          pitch-b = "15"
         flapmin                             = "-15"         flapmax = "15"
         flap0                               = "-5"       lap0factor = "0"
         notorque                            = "0"
         balance                             = "1"
         dragfactor                          = "0.3"
         translift-ve                        = "30"
         translift-maxfactor                 = "1.3"
         ground-effect-constant              = "0.1"
         taper                               = "1"
         rel-len-where-incidence-is-measured = "0.7"
         rel-len-blade-start                 = "0.076"
         airfoil-lift-coefficient            = "12.98"
         airfoil-drag-coefficient0           = "0.025"
         airfoil-drag-coefficient1           = "0.65"
         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             = "0.95"
         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="-0.20" dst1=" 0.20"/>
         <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=" 0.50" dst1="-0.08"/>

         <control-output control="CYCLICELE"  prop="/surface-positions/elevator-pos-norm"/>
  </rotor>

  <rotor name="tail"
         x                                = "-5.601" y = "-0.456" z = "1.010"
         nx                               = "0"     ny = "1"     nz = "0"
         fx                               = "1"     fy = "0"     fz = "0"
         ccw                              = "0"
         mincollective                    = "-20"   maxcollective = "14"
         diameter                         = "2.66"
         numblades                        = "2"
         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-trim"/>
         <control-input control="COLLECTIVE" axis="/controls/flight/rudder" src0="-1" src1="1" dst0="-0.10" dst1=" 0.53"/>
  </rotor>

  <!-- 2 Klimov GTD-350P turboshaft engines ( 400 hp each )

       Sources : https://www.wikiwand.com/en/PZL_GTD-350P

       Dry weight : 135 kg ( 298 lb )
  -->
  <rotorgear max-power-engine      = "400"
             max-power-rotor-brake = "100"
             rotorgear-friction    = "1.4"
             engine-prop-factor    = "0.005"
             engine-accel-limit    = "2"
             yasimdragfactor       = "18.5"
             yasimliftfactor       = "18">
             <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>

  <rotorgear max-power-engine      = "400"
             max-power-rotor-brake = "100"
             rotorgear-friction    = "1.4"
             engine-prop-factor    = "0.005"
             engine-accel-limit    = "2"
             yasimdragfactor       = "18.5"
             yasimliftfactor       = "18">
             <control-input control="ROTORGEARENGINEON"       axis="/controls/engines/engine[1]/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="4.509" y="0.394" z="-0.380"/>

  <fuselage ax=" 5.683" ay=" 0.000" az="-0.775" bx=" 4.418" by=" 0.000" bz="-0.684" width="1.527" taper="0.50" midpoint="1"/>
  <fuselage ax=" 4.418" ay=" 0.000" az="-0.063" bx=" 1.533" by=" 0.000" bz="-0.063" width="1.527" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.533" ay=" 0.000" az="-0.063" bx=" 0.481" by=" 0.000" bz="-0.044" width="1.527" taper="0.50" midpoint="0"/>
  <fuselage ax=" 0.481" ay=" 0.000" az="-0.044" bx="-3.773" by=" 0.000" bz=" 0.036" width="0.778" taper="0.40" midpoint="0"/>
  <fuselage ax="-3.773" ay=" 0.000" az=" 0.036" bx="-5.668" by=" 0.000" bz=" 1.068" width="0.332" taper="0.40" midpoint="0"/>

  <fuselage ax=" 4.418" ay=" 0.000" az="-0.683" bx=" 1.533" by=" 0.000" bz="-0.683" width="1.527" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.861" ay=" 0.000" az="-0.759" bx=" 0.637" by=" 0.000" bz="-0.071" width="1.527" taper="0.50" midpoint="0"/>

  <fuselage ax=" 4.418" ay=" 0.000" az=" 0.437" bx=" 2.975" by=" 0.000" bz=" 0.437" width="1.527" taper="0.50" midpoint="1"/>
  <fuselage ax=" 2.975" ay=" 0.000" az=" 0.437" bx=" 1.301" by=" 0.000" bz=" 0.437" width="1.527" taper="0.50" midpoint="0"/>

  <hstab x="-3.506" y="0.000" z="0.014"
         chord  = "0.526"
         length = "0.905"
         taper  = "1">
         <flap0 start="0.0" end="1.0" lift="1.7" drag="1.7"/>
         <control-input control="FLAP0" axis="/controls/flight/elevator" src0="-1" src1="1" dst0="-0.40" dst1=" 0.40"/>
  </hstab>

  <!-- front -->
  <gear x=" 4.697" y=" 0.000" z="-1.858"
        compression = "0.15"
        spring      = "8"
        stiction    = "1">
        <control-input  control="STEER"  axis="/controls/flight/rudder" src0="-1.0" src1="1.0" dst0="-0.1" dst1="0.1"/>
        <control-input  control="BRAKE"  axis="/controls/gear/brake-parking"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="6"/>
  </gear>

  <!-- Left -->
  <gear x=" 2.199" y=" 1.526" z="-1.852"
        compression = "0.15"
        spring      = "8"
        stiction    = "1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-parking"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="6.5"/>
  </gear>

  <!-- Right -->
  <gear x=" 2.199" y="-1.526" z="-1.852"
        compression = "0.15"
        spring      = "8"
        stiction    = "1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-parking"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="7"/>
  </gear>

  <!-- Tail -->
  <gear x="-4.083" y=" 0.000" z="-0.898"
        skid        = "1"
        compression = "0.1"
        spring      = "8"
        stiction    = "1">
  </gear>


  <!-- Fuel tanks 600 L (1322.77 lbs) -->
  <tank x="2.800" y=" 0.000" z="-1.300" capacity="1322.77"/>  <!-- Fuselage         -->
  <!-- External fuel tanks 238 l (524.7 lbs) each -->
  <tank x="3.314" y=" 1.088" z="-0.830" capacity=" 524.70"/>  <!-- Left External    -->
  <tank x="3.014" y="-1.088" z="-0.830" capacity=" 524.70"/>  <!-- Right External   -->

  <!-- pilot -->
  <weight x=" 4.600" y="-0.410" z="-0.870" mass-prop="/sim/weight[0]/weight-lb"/>

  <!-- co-pilot -->
  <weight x=" 4.600" y=" 0.410" z="-0.870" mass-prop="/sim/weight[1]/weight-lb"/>

  <!-- load -->
  <weight x=" 2.900" y=" 0.000" z="-1.000" mass-prop="/sim/weight[2]/weight-lb"/>

  <!-- Mass displacement  : Rotor center on x 2.866 -->
  <!-- Cockpit -->
  <ballast x=" 4.980" y=" 0.000" z=" 0.300" mass=" 990"/>
  <!-- Cargo -->
  <ballast x=" 2.600" y=" 0.000" z="-0.970" mass="2600"/>
  <!-- Engine left -->
  <ballast x=" 3.288" y=" 0.400" z=" 0.530" mass=" 298"/>
  <!-- Engine right -->
  <ballast x=" 3.288" y="-0.400" z=" 0.530" mass=" 298"/>
  <!-- Transmission -->
  <ballast x=" 2.688" y=" 0.000" z=" 1.230" mass=" 200"/>
  <!-- Tail -->
  <ballast x="-3.912" y=" 0.000" z=" 0.130" mass=" 200"/>

</airplane>
