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

<!-- Grumman Amerian AA1 -    2013 Emmanuel BARANGER
                 Updated -    2019 Emmanuel BARANGER
                 Updated - 12/2025 Emmanuel BARANGER

     sources            : http://en.wikipedia.org/wiki/Grumman_American_AA-1

     wingspan           : 24.46 ft ( 7.46 m )
     length             : 19.24 ft ( 5.87 m )
     height             :  6.80 ft ( 2.07 m )
     empty weight       :  1018 lb ( 461 kg )
     Max takeoff weight :  1500 lb ( 680 kg )
     engine             : 1 x Lycoming O-235-C2C flat-four engine ( 108 hp )
     Cruise speed       : 201 km/h ( 108.53 kt )
     Maximum speed      : 222 hm/h ( 119.87 kt )
     Never exceed speed : 314 km/h ( 169.54 kt )
-->
<airplane mass="1018" version="YASIM_VERSION_CURRENT" mtow-lbs="1500">

  <!-- Approach configuration -->
  <approach speed="44" aoa="4" fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="0.65"/>
    <control-setting axis="/controls/flight/flaps"               value="1"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise speed="109" alt="6000" fuel="0.5">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="0.65"/>
    <control-setting axis="/controls/flight/flaps"               value="0"/>
  </cruise>

  <cockpit x="0.899" y="0.176" z="0.239"/>

  <!-- Fuselage -->
  <fuselage  ax=" 2.590" ay=" 0.216" az="-0.210" bx=" 2.245" by=" 0.138" bz="-0.250" width="0.483" taper="0.20" midpoint="1"/>
  <fuselage  ax=" 2.238" ay=" 0.138" az="-0.252" bx=" 1.778" by=" 0.126" bz="-0.272" width="0.630" taper="0.72" midpoint="1"/>
  <fuselage  ax=" 1.778" ay=" 0.126" az="-0.272" bx=" 0.284" by=" 0.126" bz="-0.272" width="0.630" taper="1.00" midpoint="1"/>
  <fuselage  ax=" 0.274" ay=" 0.126" az="-0.272" bx="-2.869" by=" 0.000" bz="-0.107" width="0.630" taper="0.20" midpoint="0"/>

  <fuselage  ax=" 2.620" ay=" 0.000" az="-0.183" bx=" 2.270" by=" 0.000" bz="-0.250" width="0.475" taper="0.40" midpoint="1"/>

  <fuselage  ax=" 2.590" ay="-0.216" az="-0.210" bx=" 2.245" by="-0.138" bz="-0.250" width="0.483" taper="0.20" midpoint="1"/>
  <fuselage  ax=" 2.238" ay="-0.138" az="-0.252" bx=" 1.778" by="-0.126" bz="-0.272" width="0.630" taper="0.72" midpoint="1"/>
  <fuselage  ax=" 1.778" ay="-0.126" az="-0.272" bx=" 0.284" by="-0.126" bz="-0.272" width="0.630" taper="1.00" midpoint="1"/>
  <fuselage  ax=" 0.274" ay="-0.126" az="-0.272" bx="-2.869" by=" 0.000" bz="-0.107" width="0.630" taper="0.20" midpoint="0"/>

  <!-- Cockpit -->
  <fuselage  ax=" 1.766" ay=" 0.078" az="-0.084" bx=" 1.287" by=" 0.126" bz=" 0.065" width="0.567" taper="0.60" midpoint="1"/>
  <fuselage  ax=" 1.364" ay=" 0.126" az=" 0.065" bx=" 0.931" by=" 0.126" bz=" 0.108" width="0.630" taper="0.90" midpoint="1"/>
  <fuselage  ax=" 0.985" ay=" 0.126" az=" 0.108" bx=" 0.284" by=" 0.126" bz=" 0.031" width="0.630" taper="1.00" midpoint="1"/>
  <fuselage  ax=" 0.274" ay=" 0.126" az=" 0.032" bx="-2.869" by=" 0.000" bz="-0.107" width="0.630" taper="0.20" midpoint="0"/>

  <fuselage  ax=" 1.766" ay="-0.078" az="-0.084" bx=" 1.287" by="-0.126" bz=" 0.065" width="0.567" taper="0.60" midpoint="1"/>
  <fuselage  ax=" 1.364" ay="-0.126" az=" 0.065" bx=" 0.931" by="-0.126" bz=" 0.108" width="0.630" taper="0.90" midpoint="1"/>
  <fuselage  ax=" 0.985" ay="-0.126" az=" 0.108" bx=" 0.284" by="-0.126" bz=" 0.031" width="0.630" taper="1.00" midpoint="1"/>
  <fuselage  ax=" 0.274" ay="-0.126" az=" 0.032" bx="-2.869" by=" 0.000" bz="-0.107" width="0.630" taper="0.20" midpoint="0"/>

  <wing x="0.630" y="0.000" z="-0.418"
        chord    = "1.200"
        length   = "3.756"
        dihedral = "3.58"
        camber   = "0.06">
        <stall   aoa="20" width="1"    peak="1.5"/>
        <flap0 start="0.19" end="0.56" lift="1.2" drag="1.6"/>
        <flap1 start="0.56" end="0.94" 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="5"/>
  </wing>

  <hstab x="-2.531" y="0.000" z="-0.114"
         chord     = "0.681"
         length    = "1.098"
         taper     = "1"
         incidence = "0"
         sweep     = "0">
         <stall   aoa="18" width="1" peak="1.1"/>
         <flap0 start="0"    end="1" lift="1.4" 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="-2.290" y="0.000" z="-0.052"
         chord  = "1.129"
         length = "1.101"
         taper  = "0.4"
         sweep  = "16">
         <stall   aoa="24" width="1" peak="1.5"/>
         <flap0 start="0"    end="1" lift="1.2" 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/Lycoming_O-235

                 name              : Lycoming O-235
                 type              : 4-cylinder air-cooled horizontally opposed piston aircraft engine
                 propeller         : EVRA PE 164/152/116
                 Displacement      : 361 cu in (5916 cc)
                 power cruise      : 115 hp at 2300 rpm
                 weight            : 240.0 lb  ( 108.9 kg )
                 Displacement      : 233.3 in3 ( 3.823 L )
                 Compression ratio : 6.5:1

       noise (dB): 66,0 (ICAO chapter 10, annex 16), 76,4 (ICAO chapter 10, annex 10.4a)
  -->
  <propeller x="2.167" y="0" z="-0.225"
             mass          = "240"
             moment        = "12.9654"
             radius        = "0.659"
             cruise-speed  = "109"
             cruise-rpm    = "2300"
             cruise-alt    = "4000"
             cruise-power  = "100"
             takeoff-power = "115"
             takeoff-rpm   = "2700" >
             <actionpt x="2.71230" y="0" z="-0.18486" />
             <control-input control="MIXTURE"  axis="/controls/engines/engine[0]/mixture"/> <!-- Ground adjustment only -->
             <piston-engine eng-rpm      = "2700"
                            eng-power    = "115"
                            alt          = "4000"
                            displacement = "233.3"
                            compression  = "6.5">
                            <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"/>
             </piston-engine>
  </propeller>

  <!-- Nose wheel -->
  <gear x="2.293" y="0.000" z="-1.031"
        compression = "0.15"
        spring      = "1.1"
        damp        = "1.4"
        stiction    = "1">
        <control-input control="STEER"     axis="/controls/flight/rudder" src0="-1" src1="1" dst0="-0.8" dst1="0.8"/>
  </gear>

  <!-- Left wheel -->
  <gear x="0.875" y="0.990" z="-1.032"
        compression = "0.1"
        spring      = "0.85"
        damp        = "2"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-left" split="true"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
        <control-input control="STEER" axis="/sim/gears/toe-left"/>
  </gear>

  <!-- Right wheel -->
  <gear x="0.875" y="-0.990" z="-1.032"
        compression = "0.1"
        spring      = "0.85"
        damp        = "2"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-right" split="true"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
        <control-input control="STEER" axis="/sim/gears/toe-right"/>
  </gear>

  <!-- Fuel
       ==========
       The tank is located behind the pilot and co-pilot seats
       It has a capacity of 68 L
       Motorisation accepts Avgas 100LL or Super Sans Plomb 95 (Unlead 85 MON octan indice) without any limitation
  -->
  <tank x="0.456" y="0" z="-0.310" capacity="107.7" />

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 1.200 / 6     = 0.200
                 0.630 + 0.200 = 0.830 - 1.000 for yet
  -->
  <ballast x="1.5" y="0" z="-0.5" mass="292.5"/>

</airplane>
