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

<!-- AIRCO D.H.2  : Emmanuel BARANGER    2011
          Updated : BARANGER Emmanuel 08/2023

     Source       : https://www.wikiwand.com/en/Airco_DH.2

     Wingspan     :   28 ft 3 in     ( 8.61 m )
     Length       :   25 ft 2 1/2 in ( 7.69 m )
     Height       :    9 ft 6 1/2 in ( 2.91 m )
     Empty weight :  942 lb          ( 428 kg )
     Gross weight : 1441 lb          ( 654 kg )
     Engine       : 1 Gnome Monosoupape rotary engine (100 hp)
     Max speed    : 81.8 kt (150 km/h) at sea level
-->
<airplane mass="942" version="YASIM_VERSION_CURRENT" mtow-lbs="1441">

  <approach          speed="30" aoa="7"                          fuel="0.3">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="0.65"/>
  </approach>

  <cruise            speed="70" alt="5000"                       fuel="0.7" >
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1" />
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="0.65" />
  </cruise>

  <cockpit x="2.685" y="0.00" z="0.688"/>

  <fuselage ax=" 3.840" ay=" 0.000" az="-0.016" bx=" 3.575" by=" 0.000" bz="-0.016" width="0.672" taper="0.50" midpoint="1"/>
  <fuselage ax=" 3.575" ay=" 0.000" az="-0.016" bx=" 1.015" by=" 0.000" bz="-0.016" width="0.672" taper="1.00" midpoint="1"/>
  <fuselage ax=" 3.575" ay=" 0.000" az=" 0.159" bx=" 3.310" by=" 0.000" bz=" 0.159" width="0.672" taper="0.50" midpoint="1"/>
  <fuselage ax=" 3.310" ay=" 0.000" az=" 0.159" bx=" 1.022" by=" 0.000" bz=" 0.202" width="0.672" taper="1.00" midpoint="1"/>

  <fuselage ax=" 1.150" ay=" 1.511" az=" 1.120" bx="-2.841" by=" 0.020" bz=" 0.613" width="0.050" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.150" ay=" 1.511" az="-0.256" bx="-2.841" by=" 0.020" bz="-0.030" width="0.050" taper="1.00" midpoint="1"/>

  <fuselage ax=" 1.150" ay="-1.511" az=" 1.120" bx="-2.841" by="-0.020" bz=" 0.613" width="0.050" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.150" ay="-1.511" az="-0.256" bx="-2.841" by="-0.020" bz="-0.030" width="0.050" taper="1.00" midpoint="1"/>

  <!-- Wing up -->
  <wing x="1.362" y="0" z="1.076"
        chord    = "1.351"
        length   = "4.303"
        taper    = "1"
        dihedral = "4"
        camber   = "0.02">
        <stall   aoa="20"  width="1" peak="1.5"/>
        <flap0 start="0.574" end="1" lift="1.2" drag="1.2"/>

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

        <control-output control="FLAP0" prop="/surface-positions/left-aileron-pos-norm"  side="left"/>
        <control-output control="FLAP0" prop="/surface-positions/right-aileron-pos-norm" side="right"/>
  </wing>

  <!-- Wing down -->
  <wing x="1.362" y="0.000" z="-0.284"
        append   = "1"
        chord    = "1.351"
        length   = "4.303"
        taper    = "1"
        dihedral = "4"
        camber="0.01">
        <stall   aoa="20"  width="1" peak="1.5"/>
        <flap1 start="0.574" end="1" lift="1.2" drag="1.2"/>

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

        <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"/>
  </wing>

  <hstab x="-2.665" y="0.000" z="0.741"
         chord="1.449"
         length="1.452"
         taper="1">
         <stall   aoa="18" width="1" peak="1.5"/>
         <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="-2.882" y="0.000" z="-0.048"
         chord  = "1.476"
         length = "1.151"
         taper  = "1">
         <stall   aoa="16" width="1" peak="1.5"/>
         <flap0 start="0"    end="1" 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" min="1" max="-1"/>
  </vstab>

  <!-- Engines      : Gnome Monosoupape

       Informations : http://en.wikipedia.org/wiki/Gnome_Monosoupape

       Type         : 9-cylinder, single-row, rotary engine
       Power        :   100 hp at 1300 rpm (Maximum power)
       Displacement :  12.8 L     ( 781.63 in3 )
       Diameter     :    95 cm    (  37.40 in  )
       Masse        : 137.4 kg    ( 303.00 lb  )
  -->
  <propeller x="1.000" y="0" z="0.232"
             radius        = "1.276"
             mass          = "303"
             moment        = "-4"
             cruise-power  = "100"
             cruise-alt    = "5000"
             cruise-speed  = "70"
             cruise-rpm    = "1100"
             takeoff-power = "100"
             takeoff-rpm   = "1300">
             <actionpt x="0.770" y="0.000" z="0.232"/>
             <piston-engine eng-power    = "100"
                            eng-rpm      = "1300"
                            alt          = "5000"
                            displacement = "781.63">
                            <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="MIXTURE"  axis="/controls/engines/engine[0]/mixture"/>
             </piston-engine>
  </propeller>

  <!-- Left wheel -->
  <gear x="1.936" y="0.907" z="-1.455"
        compression = "0.10"
        spring      = "2"
        damp        = "1"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-left"    split="true"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
  </gear>

  <!-- Right wheel -->
  <gear x="1.936" y="-0.907" z="-1.455"
        compression = "0.10"
        spring      = "2"
        damp        = "1"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-right"   split="true"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
  </gear>

  <!-- Tail wheel -->
  <gear x="-3.217" y="0" z="-0.456"
        compression = "0.05"
        spring      = "2"
        damp        = "1"
        stiction    = "1">
        <control-input axis="/controls/flight/rudder" control="STEER" src0="-1.0" src1="1.0" dst0="0.8" dst1="-0.8"/>
  </gear>

  <!-- Fuel: Forward 142 lbs -->
  <tank x="1.824" y="0.000" z="0.200" capacity="142"/>

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 1.351 / 6     = 0.225
                 1.362 + 0.225 = 1.587
  -->
  <ballast x="3.600" y="0.000" z="-0.200" mass="254.5"/>

</airplane>
