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

<!-- Dassault Falcon 50 : BARANGER Emmanuel            (   2011)
                        : Updated by Jano              (   2011)
                        : Updated by BARANGER Emmanuel (04/2011)
                        : Updated by BARANGER Emmanuel (07/2024)

     sources            : http://en.wikipedia.org/wiki/Dassault_Falcon_50

     Wingspan           : 18.86 m    (    61 ft 10 1/2 in  )
     Lenght             : 18.52 m    (    60 ft  9 1/4 in  )
     Height             :  6.97 m    (    22 ft 10 1/2 in  )
     Empty mass         :  9150 kg   ( 20170 lb            )
     Max takeoff weight : 18008 kg   ( 39701 lb            )
     Engines            : 3 Garrett TFE731-3-1C turbofan engines (3700 lbf each)
     Cruise speed       : Mach 0.82  ( 888 km/h / 484.0 kt )
     Maximim speed      : Mach 0.86  ( 915 km/h / 498.7 kt )
-->
<airplane mass="20170" version="YASIM_VERSION_CURRENT" mtow-lbs="39701">

  <approach speed="110" aoa="4" fuel="0.7">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
    <control-setting axis="/controls/engines/engine[1]/throttle" value="0.2"/>
    <control-setting axis="/controls/engines/engine[2]/throttle" value="0.2"/>
    <control-setting axis="/controls/flight/flaps"               value="1"/>
    <control-setting axis="/controls/gear/gear-down"             value="1"/>
  </approach>

  <cruise speed="484" alt="19500" fuel="1">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.8"/>
    <control-setting axis="/controls/engines/engine[1]/throttle" value="0.8"/>
    <control-setting axis="/controls/engines/engine[2]/throttle" value="0.8"/>
    <control-setting axis="/controls/flight/flaps"               value="0"/>
    <control-setting axis="/controls/gear/gear-down"             value="0"/>
  </cruise>

  <cockpit x="7.063" y="0.385" z="-0.837"/>

  <!-- Fuselage -->
  <fuselage ax=" 9.252" ay=" 0.000" az="-1.828" bx=" 9.054" by=" 0.000" bz="-1.800" width="0.423" taper="0.15" midpoint="1"/>
  <fuselage ax="-5.924" ay=" 0.000" az="-1.097" bx="-7.884" by=" 0.000" bz="-0.969" width="1.580" taper="0.45" midpoint="0"/>
  <fuselage ax="-7.884" ay=" 0.000" az="-0.969" bx="-8.325" by=" 0.000" bz="-0.937" width="0.711" taper="0.60" midpoint="0"/>

  <!-- left down -->
  <fuselage ax=" 9.054" ay=" 0.000" az="-1.800" bx=" 8.756" by=" 0.029" bz="-1.757" width="0.691" taper="0.60" midpoint="1"/>
  <fuselage ax=" 8.756" ay=" 0.029" az="-1.757" bx=" 8.283" by=" 0.103" bz="-1.709" width="0.963" taper="0.70" midpoint="1"/>
  <fuselage ax=" 8.283" ay=" 0.103" az="-1.709" bx=" 7.666" by=" 0.189" bz="-1.625" width="1.229" taper="0.80" midpoint="1"/>
  <fuselage ax=" 7.666" ay=" 0.189" az="-1.625" bx=" 6.491" by=" 0.270" bz="-1.633" width="1.443" taper="0.84" midpoint="1"/>
  <fuselage ax=" 6.491" ay=" 0.270" az="-1.633" bx="-2.825" by=" 0.270" bz="-1.633" width="1.443" taper="1.00" midpoint="1"/>
  <fuselage ax="-2.825" ay=" 0.270" az="-1.633" bx="-5.924" by=" 0.074" bz="-1.168" width="1.443" taper="1.00" midpoint="1"/>
  <!-- left up -->
  <fuselage ax=" 7.727" ay=" 0.270" az="-1.425" bx=" 6.276" by=" 0.270" bz="-1.007" width="1.443" taper="0.50" midpoint="1"/>
  <fuselage ax=" 6.491" ay=" 0.270" az="-1.027" bx="-2.825" by=" 0.270" bz="-1.027" width="1.443" taper="1.00" midpoint="1"/>
  <fuselage ax="-2.825" ay=" 0.270" az="-1.027" bx="-5.870" by=" 0.074" bz="-1.027" width="1.443" taper="1.00" midpoint="1"/>

  <!-- right sown -->
  <fuselage ax=" 9.054" ay=" 0.000" az="-1.800" bx=" 8.756" by="-0.029" bz="-1.757" width="0.691" taper="0.60" midpoint="1"/>
  <fuselage ax=" 8.756" ay="-0.029" az="-1.757" bx=" 8.283" by="-0.103" bz="-1.709" width="0.963" taper="0.70" midpoint="1"/>
  <fuselage ax=" 8.283" ay="-0.103" az="-1.709" bx=" 7.666" by="-0.189" bz="-1.625" width="1.229" taper="0.80" midpoint="1"/>
  <fuselage ax=" 7.666" ay="-0.189" az="-1.625" bx=" 6.491" by="-0.270" bz="-1.633" width="1.443" taper="0.84" midpoint="1"/>
  <fuselage ax=" 6.491" ay="-0.270" az="-1.633" bx="-2.825" by="-0.270" bz="-1.633" width="1.443" taper="1.00" midpoint="1"/>
  <fuselage ax="-2.825" ay="-0.270" az="-1.633" bx="-5.924" by="-0.074" bz="-1.168" width="1.443" taper="1.00" midpoint="1"/>

  <!-- left up -->
  <fuselage ax=" 7.727" ay="-0.270" az="-1.425" bx=" 6.276" by="-0.270" bz="-1.007" width="1.443" taper="0.50" midpoint="1"/>
  <fuselage ax=" 6.491" ay="-0.270" az="-1.027" bx="-2.825" by="-0.270" bz="-1.027" width="1.443" taper="1.00" midpoint="1"/>
  <fuselage ax="-2.825" ay="-0.270" az="-1.027" bx="-5.870" by="-0.074" bz="-1.027" width="1.443" taper="1.00" midpoint="1"/>

  <!-- Left engine -->
  <fuselage ax="-1.807" ay=" 1.537" az="-1.060" bx="-2.051" by=" 1.537" bz="-1.060" width="0.960" taper="0.70" midpoint="1"/>
  <fuselage ax="-2.051" ay=" 1.537" az="-1.060" bx="-2.296" by=" 1.537" bz="-1.060" width="1.028" taper="0.94" midpoint="1"/>
  <fuselage ax="-2.296" ay=" 1.537" az="-1.060" bx="-2.833" by=" 1.537" bz="-1.060" width="1.033" taper="0.99" midpoint="1"/>
  <fuselage ax="-2.833" ay=" 1.537" az="-1.060" bx="-3.516" by=" 1.537" bz="-1.060" width="1.033" taper="0.89" midpoint="0"/>
  <fuselage ax="-3.516" ay=" 1.537" az="-1.060" bx="-4.199" by=" 1.537" bz="-1.060" width="0.922" taper="0.72" midpoint="0"/>
  <fuselage ax="-4.199" ay=" 1.537" az="-1.060" bx="-4.337" by=" 1.537" bz="-1.060" width="0.668" taper="0.60" midpoint="0"/>

  <!-- Center engine -->
  <fuselage ax="-1.535" ay=" 0.000" az=" 0.203" bx="-1.779" by=" 0.000" bz=" 0.203" width="0.960" taper="0.70" midpoint="1"/>
  <fuselage ax="-1.779" ay=" 0.000" az=" 0.203" bx="-2.024" by=" 0.000" bz=" 0.203" width="1.028" taper="0.94" midpoint="1"/>
  <fuselage ax="-2.024" ay=" 0.000" az=" 0.203" bx="-4.003" by=" 0.000" bz=" 0.203" width="1.028" taper="0.99" midpoint="0"/>
  <fuselage ax="-4.003" ay=" 0.000" az=" 0.203" bx="-5.971" by=" 0.000" bz=" 0.203" width="1.018" taper="0.60" midpoint="0"/>

  <!-- Right engine -->
  <fuselage ax="-1.807" ay="-1.537" az="-1.060" bx="-2.051" by="-1.537" bz="-1.060" width="0.960" taper="0.70" midpoint="1"/>
  <fuselage ax="-2.051" ay="-1.537" az="-1.060" bx="-2.296" by="-1.537" bz="-1.060" width="1.028" taper="0.94" midpoint="1"/>
  <fuselage ax="-2.296" ay="-1.537" az="-1.060" bx="-2.833" by="-1.537" bz="-1.060" width="1.033" taper="0.99" midpoint="1"/>
  <fuselage ax="-2.833" ay="-1.537" az="-1.060" bx="-3.516" by="-1.537" bz="-1.060" width="1.033" taper="0.89" midpoint="0"/>
  <fuselage ax="-3.516" ay="-1.537" az="-1.060" bx="-4.199" by="-1.537" bz="-1.060" width="0.922" taper="0.72" midpoint="0"/>
  <fuselage ax="-4.199" ay="-1.537" az="-1.060" bx="-4.337" by="-1.537" bz="-1.060" width="0.668" taper="0.60" midpoint="0"/>

  <wing x="0.210" y="0" z="-2.111"
        chord="4.724"
        length="3.782"
        taper="0.538"
        sweep="20.4"
        camber="0.08">
        <stall   aoa="22" width="1" peak="1.5"/>
        <flap0 start="0.25" end="1" lift="1.5" drag="1.70"/>
        <slat  start="0.00" end="1"  aoa="3.0" drag="1.20"/>

        <control-input  control="FLAP0" axis="/controls/flight/flaps" src0="0.4" src1="1"   dst0="0" dst1="1"/>
        <control-input  control="SLAT"  axis="/controls/flight/flaps" src0="0"   src1="0.4" dst0="0" dst1="1"/>

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

        <control-speed  control="FLAP0" transition-time="30"/>
  </wing>

  <wing x="-1.103" y="3.541" z="-2.111"
        append="1"
        chord="2.549"
        length="6.35"
        taper="0.46"
        sweep="21.8"
        idrag="1.0"
        twist="-2.5"        >
        <stall     aoa="22"   width="1"     peak="1.5"/>
        <spoiler start="0.1374" end="0.613" lift="0.0" drag="25"/>
        <flap0   start="0.0800" end="0.615" lift="1.5" drag="1.70"/>
        <flap1   start="0.6240" end="0.959" lift="1.3" drag="1.05"/>
        <slat    start="0.0000" end="1.000"  aoa="3.0" drag="1.20"/>

        <control-input  control="SPOILER" axis="/controls/flight/spoilers"/>
        <control-input  control="FLAP0"   axis="/controls/flight/flaps"        src0="0.4" src1="1"   dst0="0" dst1="1"/>
        <control-input  control="SLAT"    axis="/controls/flight/flaps"        src0="0"   src1="0.4" dst0="0" dst1="1"/>
        <control-input  control="FLAP1"   axis="/controls/flight/aileron"      square="true" split="true"/>
        <control-input  control="FLAP1"   axis="/controls/flight/aileron-trim" split="true"/>

        <control-output control="SPOILER" prop="/surface-positions/speedbrake-pos-norm"/>
        <control-output control="FLAP0"   prop="/surface-positions/flap-pos-norm"/>
        <control-output control="FLAP1"   prop="/surface-positions/left-aileron-pos-norm"  side="left"/>
        <control-output control="FLAP1"   prop="/surface-positions/right-aileron-pos-norm" side="right"/>
        <control-output control="SLAT"    prop="/surface-positions/slat-pos-norm"/>

        <control-speed  control="FLAP0"   transition-time="5"/>
        <control-speed  control="SLAT"    transition-time="3"/>
        <control-speed  control="SPOILER" transition-time="3"/>
  </wing>

  <hstab x="-6.559" y="0" z="0.534"
         chord="2.430"
         length="4.2"
         taper="0.44"
         sweep="30"
         dihedral="0.0"
         incidence="-0.2">
         <stall   aoa="22" width="1"    peak="2.5"/>
         <flap0 start="0.05" end="0.67" lift="2.2" drag="1.2"/>

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

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

  <vstab x="-5.457" y="0" z="-0.445"
         chord="3.551"
         length="4.7"
         taper="0.4"
         sweep="32">
         <stall   aoa="16" width="1"   peak="1.5"/>
         <flap0 start="0.3"  end="0.9" lift="1.4" drag="1.2"/>

         <control-input  control="FLAP0" axis="/controls/flight/rudder"      invert="true"/>
         <control-input  control="FLAP0" axis="/controls/flight/rudder-trim" invert="true"/>
         <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
  </vstab>

  <!-- Engines   source            : http://en.wikipedia.org/wiki/Honeywell_TFE731

                 name              : Garrett TFE731
                 type              : Turbofan
                 power cruise      : 3500 lbf
                 weight            : 734 lb ( 333 kg )
  -->
  <jet x="-3.075" y="1.537" z="-1.060"
       mass="734"
       thrust="3500"
       tsfc="0.576">
       <actionpt x="-4.343" y="1.537" z="-1.060"/>
       <control-input  control="THROTTLE"       axis="/controls/engines/engine[0]/throttle"/>
       <control-input  control="REVERSE_THRUST" axis="/controls/engines/engine[0]/reverser"/>

       <control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm"/>

       <control-speed  control="REVERSE_THRUST" transition-time="1.5"/>
  </jet>

  <jet x="-3.075" y="-1.537" z="-1.060"
       mass="734"
       thrust="3500"
       tsfc="0.576">
       <actionpt x="-4.343" y="-1.537" z="-1.060"/>
       <control-input  control="THROTTLE"       axis="/controls/engines/engine[1]/throttle"/>
       <control-input  control="REVERSE_THRUST" axis="/controls/engines/engine[1]/reverser"/>

       <control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm"/>

       <control-speed  control="REVERSE_THRUST" transition-time="1.5"/>
  </jet>

  <jet x="-2.941" y="0.000" z="0.203"
       mass="734"
       thrust="3500"
       tsfc="0.576">
       <actionpt x="-8.324" y="0.000" z="-0.946"/>
       <control-input  control="THROTTLE"       axis="/controls/engines/engine[2]/throttle"/>
       <control-input  control="REVERSE_THRUST" axis="/controls/engines/engine[2]/reverser"/>

       <control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm"/>

       <control-speed  control="REVERSE_THRUST" transition-time="1.5"/>
  </jet>

  <!-- nose -->
  <gear x="6.201" y="0" z="-3.475"
        compression="0.2"
        spring="1.1"
        damp="1.4"
        stiction="1">
        <control-input  control="STEER"  axis="/controls/flight/rudder" square="true" src0="-1.0" src1="1.0" dst0="-0.9" dst1="0.9"/>
        <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="7"/>
  </gear>

  <!-- left main -->
  <gear x="-0.976" y="1.888" z="-3.469"
        compression="0.2"
        spring="0.85"
        damp="2"
        stiction="1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-left"/>
        <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="7"/>
  </gear>

  <!-- right main -->
  <gear x="-0.976" y="-1.888" z="-3.469"
        compression="0.2"
        spring="0.85"
        damp="2"
        stiction="1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-right"/>
        <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>

  <!-- Internal tanks
       2*280 liter wings

       2*280 = 560 litres = 1234.5 lbs = 147,936 gal us
  -->
  <tank x="0.160" y=" 1.500" z="-2.130" jet="true" capacity="1234.5"/>
  <tank x="0.160" y=" 0.000" z="-2.130" jet="true" capacity="1234.5"/>
  <tank x="0.160" y="-1.500" z="-2.130" jet="true" capacity="1234.5"/>

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 4.724 / 6     = 0.787
                 0.210 + 0.787 = 0.997
  -->
  <ballast x=" 8.500" y=" 0.000" z="-1.900" mass="5252"/>

</airplane>
