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

<!-- Socata TBM 930 :    2019 Emmanuel BARANGER
            Updated : 12/2022 Emmanuel BARANGER
                      12/2025 Paolo    AMOROSO

     sources            : https://fr.wikipedia.org/wiki/Daher-Socata_TBM_900
                          https://en.wikipedia.org/wiki/SOCATA_TBM

     wingspan           :  12.82 m   ( 42 ft 06 in )
     length             :  10.71 m   ( 32 ft 80 in )
     height             :   4.60 m   ( 13 ft 12 in )
     empty weight       :  2111 kg   ( 4654 lb     )
     Max takeoff weight :  3354 kg   ( 7394 lb     )
     engine             : Pratt & Whitney Canada PT6A-66BD turboprop ( 850 hp )
     decrochage         :   120 km/h (  64 kts     )
     Maximum speed      :   611 km/h ( 330 Kts     )
     Cruise speed       :   467 km/h ( 252 kts     )
     Fuel capacity      :  1100 l    ( 290 US gal  ) usable
-->
<airplane mass="4654" version="YASIM_VERSION_CURRENT" mtow-lbs="7394">

  <!-- Approach configuration -->
  <approach          speed="70" aoa="2"                                 fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle"        value="0.2"/>
    <control-setting axis="/controls/engines/engine[0]/condition"       value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.3"/>
    <control-setting axis="/controls/gear/gear-down"                    value="1.0"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise            speed="252" alt="0"                                fuel="0.5">
    <control-setting axis="/controls/engines/engine[0]/throttle"        value="0.8"/>
    <control-setting axis="/controls/engines/engine[0]/condition"       value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.9"/>
    <control-setting axis="/controls/gear/gear-down"                    value="0.0"/>
  </cruise>

  <cockpit x="1.287" y="0.314" z="0.031"/>

  <!-- Bol -->
  <fuselage ax=" 5.351" ay=" 0.000" az="-0.639" bx=" 5.040" by=" 0.000" bz="-0.639" width="0.343" taper="0.10" midpoint="1"/>
  <fuselage ax=" 5.040" ay=" 0.000" az="-0.639" bx=" 4.727" by=" 0.000" bz="-0.639" width="0.500" taper="0.70" midpoint="1"/>

  <!-- Fuselage center -->
  <fuselage ax=" 4.727" ay=" 0.000" az="-0.639" bx=" 4.190" by=" 0.000" bz="-0.639" width="0.667" taper="0.75" midpoint="1"/>
  <fuselage ax=" 4.190" ay=" 0.000" az="-0.639" bx=" 2.330" by=" 0.000" bz="-0.639" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.330" ay=" 0.000" az="-0.639" bx="-0.150" by=" 0.000" bz="-0.639" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay=" 0.000" az="-0.639" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>
  <fuselage ax="-2.923" ay=" 0.000" az="-0.130" bx="-5.304" by=" 0.000" bz=" 0.094" width="0.748" taper="0.15" midpoint="0"/>
  <!-- Fuselage left up -->
  <fuselage ax=" 4.665" ay=" 0.008" az="-0.639" bx=" 4.147" by=" 0.100" bz="-0.675" width="0.773" taper="0.65" midpoint="1"/>
  <fuselage ax=" 4.190" ay=" 0.151" az="-0.639" bx=" 2.332" by=" 0.238" bz="-0.639" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.332" ay=" 0.238" az="-0.639" bx="-0.150" by=" 0.238" bz="-0.639" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay=" 0.238" az="-0.639" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>
  <!-- Fuselage right up -->
  <fuselage ax=" 4.665" ay="-0.008" az="-0.639" bx=" 4.147" by="-0.100" bz="-0.675" width="0.773" taper="0.65" midpoint="1"/>
  <fuselage ax=" 4.190" ay="-0.151" az="-0.639" bx=" 2.332" by="-0.238" bz="-0.639" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.332" ay="-0.238" az="-0.639" bx="-0.150" by="-0.238" bz="-0.639" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay="-0.238" az="-0.639" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>

  <!-- Fuselage center down -->
  <fuselage ax=" 4.633" ay=" 0.000" az="-0.910" bx=" 4.096" by=" 0.000" bz="-0.910" width="0.667" taper="0.75" midpoint="1"/>
  <fuselage ax=" 4.190" ay=" 0.000" az="-0.989" bx=" 2.334" by=" 0.000" bz="-0.859" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.334" ay=" 0.000" az="-0.859" bx="-0.150" by=" 0.000" bz="-0.859" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay=" 0.000" az="-0.859" bx="-2.928" by=" 0.000" bz="-0.336" width="0.935" taper="0.80" midpoint="0"/>
  <fuselage ax="-2.928" ay=" 0.000" az="-0.336" bx="-5.304" by=" 0.000" bz=" 0.094" width="0.748" taper="0.15" midpoint="0"/>
  <!-- Fuselage left down -->
  <fuselage ax=" 4.571" ay=" 0.008" az="-0.910" bx=" 4.053" by=" 0.100" bz="-0.946" width="0.773" taper="0.65" midpoint="1"/>
  <fuselage ax=" 4.190" ay=" 0.151" az="-0.989" bx=" 2.336" by=" 0.238" bz="-0.859" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.336" ay=" 0.238" az="-0.859" bx="-0.150" by=" 0.151" bz="-0.859" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay=" 0.151" az="-0.859" bx="-2.928" by=" 0.000" bz="-0.336" width="0.935" taper="0.80" midpoint="0"/>
  <!-- Fuselage right down -->
  <fuselage ax=" 4.571" ay="-0.008" az="-0.910" bx=" 4.053" by="-0.100" bz="-0.946" width="0.773" taper="0.65" midpoint="1"/>
  <fuselage ax=" 4.190" ay="-0.151" az="-0.989" bx=" 2.336" by="-0.238" bz="-0.859" width="0.935" taper="0.70" midpoint="1"/>
  <fuselage ax=" 2.336" ay="-0.238" az="-0.859" bx="-0.150" by="-0.151" bz="-0.859" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax="-0.150" ay="-0.151" az="-0.859" bx="-2.928" by=" 0.000" bz="-0.336" width="0.935" taper="0.80" midpoint="0"/>

  <!-- Cabin -->
  <fuselage ax="-0.103" ay=" 0.000" az="-0.149" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>
  <fuselage ax=" 1.342" ay=" 0.000" az="-0.149" bx="-0.103" by=" 0.000" bz="-0.149" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.325" ay=" 0.000" az="-0.245" bx=" 1.342" by=" 0.000" bz="-0.149" width="0.935" taper="0.15" midpoint="1"/>
  <!-- Left -->
  <fuselage ax="-0.103" ay=" 0.238" az="-0.149" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>
  <fuselage ax=" 1.342" ay=" 0.238" az="-0.149" bx="-0.103" by=" 0.238" bz="-0.149" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.325" ay=" 0.238" az="-0.245" bx=" 1.342" by=" 0.238" bz="-0.149" width="0.935" taper="0.15" midpoint="1"/>
  <!-- Right -->
  <fuselage ax="-0.103" ay="-0.238" az="-0.149" bx="-2.923" by=" 0.000" bz="-0.130" width="0.935" taper="0.80" midpoint="0"/>
  <fuselage ax=" 1.342" ay="-0.238" az="-0.149" bx="-0.103" by="-0.238" bz="-0.149" width="0.935" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.325" ay="-0.238" az="-0.245" bx=" 1.342" by="-0.238" bz="-0.149" width="0.935" taper="0.15" midpoint="1"/>

  <wing x="0.612" y="0.000" z="-1.223"
        chord    = "1.952"
        length   = "6.284"
        taper    = "0.55"
        dihedral = "7"
        sweep    = "-1.5"
        camber   = "0.001">
        <stall   aoa="20" width="1"    peak="1.5"/>
        <flap0 start="0.13" end="0.76" lift="1.4" drag="2.5"/>
        <flap1 start="0.76" end="0.98" lift="1.2" drag="1.2"/>

        <control-input  control="FLAP0" axis="/controls/flight/flaps"/>
        <control-input  control="FLAP1" axis="/controls/flight/aileron"                  split="true"/>
        <control-input  control="FLAP1" axis="/controls/flight/aileron-trim"             split="true"/>

        <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-speed  control="FLAP0" transition-time="2"/>
  </wing>

  <wing x="0.500" y="6.235" z="-0.457"
        append   = "1"
        chord    = "1.184"
        length   = "0.8"
        taper    = "0.25"
        dihedral = "45"
        sweep    = "45">
        <stall aoa="20" width="1" peak="1.5"/>
  </wing>

  <hstab x="-4.718" y="0.000" z="0.092"
         chord    = "1.2"
         length   = "2.638"
         dihedral = "7"
         taper    = "0.7">
         <stall   aoa="18" width="1" peak="1.5"/>
         <flap0 start="0"    end="1" lift="1.2" drag="1.1"/>

         <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="-3.593" y="0.000" z="0.303"
         chord  = "2"
         length = "2.5"
         taper  = "0.3"
         sweep  = "40">
         <stall   aoa="16" width="1"   peak="1.5"/>
         <flap0 start="0.02" end="0.9" lift="1.2" drag="1.1"/>

         <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/Pratt_%26_Whitney_Canada_PT6A
                                   : http://www.pwc.ca/en/engines/pt6a-67b

                 Name              : Pratt & Whitney Canada PT6
                 Type              : Turboprop
                 Weight            : 270 lb ( 122.47 kg )
                 Maximum power     : 1200 hp equivalent power at 2000 output rpm for take-off
                 Pressure ratio    : 6.3:1
 gear-ratio="0.66"
  -->
  <propeller x="3.693" y="0.000" z="-0.784"
             mass         = "270"
             moment       = "73.211"
             radius       = "1.16"
             cruise-speed = "330"
             cruise-rpm   = "1500"
             cruise-power = "800"
             cruise-alt   = "19000"
             min-rpm      = "150"
             max-rpm      = "2200"
             fine-stop    = "0.25"
             coarse-stop  = "3">
             <actionpt x="4.879" y="0.000" z="-0.639"/>
             <control-input control="ADVANCE" axis="/controls/engines/engine[0]/propeller-pitch"/>
             <turbine-engine eng-power    = "850"
                             eng-rpm      = "2000"
                             alt          = "19000"
                             flat-rating  = "1200"
                             n2-low-idle  = "32"
                             n2-high-idle = "65"
                             n2-max       = "100"
                             bsfc         = "0.35"
                             compression  = "8.7">
                             <control-input control="CONDLEVER" axis="/controls/engines/engine[0]/condition"/>
                             <control-input control="THROTTLE"  axis="/controls/engines/engine[0]/throttle"/>
                             <control-input control="STARTER"   axis="/controls/engines/engine[0]/starter"/>
                             <control-input control="MAGNETOS"  axis="/controls/engines/engine[0]/magnetos"/>
                             <control-input control="BOOST"     axis="/controls/engines/engine[0]/boost"/>
             </turbine-engine>
  </propeller>

  <!-- Noze wheel -->
  <gear x="3.663" y=" 0.000" z="-2.163"
        compression = "0.15"
        spring      = "2"
        damp        = "1"
        stiction    = "1">
        <control-input  control="STEER"  axis="/controls/flight/rudder" square="false"/>
        <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 wheel -->
  <gear x="0.751" y="-1.917" z="-2.166"
        compression = "0.2"
        spring      = "2"
        damp        = "1"
        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 wheel -->
  <gear x="0.751" y=" 1.917" z="-2.166"
        compression = "0.2"
        spring      = "2"
        damp        = "1"
        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>

  <tank x="0.680" y=" 2.580" z="-0.850" capacity="650"/>
  <tank x="1.000" y=" 0.000" z="-1.000" capacity="650"/>
  <tank x="0.680" y="-2.580" z="-0.850" capacity="650"/>

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 1.952 / 6     = 0.325
                 0.612 + 0.325 = 0.937
  -->
  <ballast x=" 4.000" y="0.000" z="-1.100" mass="916"/>

</airplane>
