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

<!-- Bell 206 Jet Ranger         : BARANGER Emmanuel 08/2025

    sources                      : https://www.wikiwand.com/en/articles/Bell_206

    Length                       :    38 ft 9.5 in ( 11.824 m  ) including rotor
    Fuselage length              :    31 ft 2   in (  9.50  m  )
    Height                       :     9 ft 6.5 in (  2.908 m  ) overall
    Empty weight                 :  1455 lb        (    660 kg )
    Max takeoff weight           :  3200 lb        (   1451 kg )
    Powerplant                   :  1 Allison 250-C20 turboshaft engine ( 400 hp )
    Main rotor diameter          :     33 ft 4 in  (  10.16 m  )
    Maximum speed                :   226 km/h      (    122 kn ) at MTOW (sea level)
    Cruise speed                 ;   220 km/h      (    120 kn ) at MTOW, 5000 feet
-->
<airplane mass="1455" version="YASIM_VERSION_CURRENT" mtow-lbs="3200">

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

  <cruise speed="120" alt="100">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1"/>
  </cruise>

  <rotor name="main"
         x  = "0.760" y  = "0.00" z  = "0.916"
         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                            = "10.30"
         numblades                           = "2"
         weightperblade                      = "200"
         relbladecenter                      = "0.6"
         dynamic                             = "1"
         rpm                                 = "380"
         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                               = "-10"
         notorque                            = "0"
         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="-0.50" dst1=" 0.50"/>
         <control-input control="CYCLICELE"  axis="/controls/flight/elevator"             src0="-1" src1="1" dst0="-0.30" dst1=" 0.30"/>
         <control-input control="COLLECTIVE" axis="/controls/engines/engine[0]/throttle"  src0=" 0" src1="1" dst0=" 0.70" dst1="-0.08"/>
  </rotor>

  <rotor name="tail"
         x  = "-5.152" y = " 0.327" z = "0.050"
         nx = "0"     ny = "1"     nz = "0"
         fx=  "1"     fy = "0"     fz = "0"
         ccw                              = "0"
         diameter                         = "1.7"
         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="-0.10" dst1=" 0.40"/>
         <control-input control="COLLECTIVE" axis="/controls/engines/engine[0]/throttle" src0=" 0" src1="1" dst0=" 0.24" dst1="-0.02"/>
  </rotor>

  <!-- Engines source            : https://www.wikiwand.com/en/articles/Allison_250

               name              : Allison Model 250
               type              : Turboshaft
               power cruise      : 317 hp
               weight            : 138.5 lb ( 63 kg )
  -->
  <rotorgear max-power-engine      = "317"
             max-power-rotor-brake = "100"
             engine-prop-factor    = "0.01"
             rotorgear-friction    = "1.005"
             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>

  <cockpit x="2.250" y="-0.250" z="-0.134"/>

  <cockpit x="2.250" y=" 0.250" z="-0.134"/>

  <!-- Fuse left up -->
  <fuselage ax=" 3.597" ay=" 0.000" az="-0.748" bx=" 3.082" by=" 0.000" bz="-0.720" width="0.717" taper="0.20" midpoint="1"/>
  <fuselage ax=" 3.087" ay=" 0.000" az="-0.727" bx=" 1.909" by=" 0.000" bz="-0.503" width="1.467" taper="0.50" midpoint="1"/>
  <fuselage ax=" 1.870" ay=" 0.000" az="-0.518" bx=" 0.947" by=" 0.000" bz="-0.331" width="1.745" taper="0.85" midpoint="1"/>
  <fuselage ax=" 0.992" ay=" 0.000" az="-0.332" bx="-0.935" by=" 0.000" bz="-0.259" width="1.750" taper="0.84" midpoint="0"/>
  <fuselage ax="-1.017" ay=" 0.000" az="-0.245" bx="-1.682" by=" 0.000" bz="-0.114" width="1.471" taper="0.40" midpoint="0"/>
  <fuselage ax="-1.678" ay=" 0.000" az="-0.101" bx="-5.618" by=" 0.000" bz="-0.014" width="0.502" taper="0.30" midpoint="0"/>

  <hstab x="-3.132" y="0" z="-0.142"
         chord  = "0.407"
         length = "1.000"
         taper  = "1">
         <stall aoa="14" width="0" peak="1.5"/>
  </hstab>

  <vstab x="-5.105" y="-0.147" z=" 0.004"
         chord     = "0.60"
         length    = "1.29"
         taper     = "0.5"
         sweep     = "20"
         incidence = "5">
         <stall aoa="16" width="1" peak="1.5"/>
  </vstab>

  <vstab x="-5.105" y="-0.147" z=" 0.004"
         chord     = "0.60"
         length    = "1.00"
         taper     = "0.5"
         dihedral  = "270"
         sweep     = "24"
         incidence = "5">
         <stall aoa="16" width="1" peak="1.5"/>
  </vstab>

  <!-- front gear 0 1 -->
  <gear x="2.33" y="0.95" z="-1.66"
        compression = "0.05"
        skid        = "1"
        spring      = "12"
        damp        = "8"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <gear x="0.2" y="0.95" z="-1.66"
        compression = "0.05"
        skid        = "1"
        spring      = "12"
        damp        = "8"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <!-- rear gear 2 3 -->
  <gear x="2.33" y="-0.95" z="-1.66"
        compression = "0.05"
        skid        = "1"
        spring      = "12"
        damp        = "8"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <gear x="0.2" y="-0.95" z="-1.66"
        compression = "0.05"
        skid        = "1"
        spring      = "12"
        damp        = "8"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <gear x="-5.824" y="-0.142" z="-1.020"
        compression = "0.01"
        skid        = "1"
        spring      = "12"
        damp        = "8"
        stiction    = "1">
  </gear>

  <!-- 735 L - 194 Gal US - 1164 lbs -->
  <tank x="0.33" y="0" z="-1.04" capacity="1164"/>

  <!-- pilot -->
  <weight x="2.250" y="-0.250" z="-0.580" mass-prop="/sim/weight[0]/weight-lb"/>

  <!-- co-pilot -->
  <weight x="2.250" y=" 0.250" z="-0.580" mass-prop="/sim/weight[1]/weight-lb"/>

  <!-- load -->
  <weight x="1.460" y=" 0.000" z="-0.630" mass-prop="/sim/weight[2]/weight-lb"/>

  <!-- Mass displacement  : Rotor center on x 0.760 -->
  <ballast x=" 3.162" y="-1.300" z="-1.130" mass="080"/>
  <ballast x=" 3.162" y=" 1.300" z="-1.130" mass="080"/>
  <ballast x=" 3.162" y="-1.300" z=" 0.270" mass="075"/>
  <ballast x=" 3.162" y=" 1.300" z=" 0.270" mass="075"/>

  <ballast x="-0.750" y="-1.300" z="-1.130" mass="010"/>
  <ballast x="-0.750" y=" 1.300" z="-1.130" mass="010"/>
  <ballast x="-0.750" y="-1.300" z=" 0.270" mass="010"/>
  <ballast x="-0.750" y=" 1.300" z=" 0.270" mass="010"/>

</airplane>
