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

<!-- Gotha G.V   : Emmanuel BARANGER    2013
          Update : Emmanuel BARANGER 03/2026

       source          : https://www.wikiwand.com/en/Gotha_G.V

       wingspan        : 23.70 m    (   77 ft 9 in )
       lenght          : 12.42 m    (   40 ft 8 in )
       height          :  4.50 m    (   14 ft      )
       Empty weight    :  2739 kg   ( 6039 lb      )
       Gross weight    :  3975 kg   ( 8763 lb      )
       engines         : 2 Mercedes D.IVa inline engine ( 260 hp each )
       max speed       :   140 km/h (   76 kt      )
-->

<airplane mass="6039" version="YASIM_VERSION_CURRENT" mtow-lbs="8763">

  <approach          speed="45" aoa="2"                          fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.4"/>
    <control-setting axis="/controls/engines/engine[1]/throttle" value="0.4"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="1"/>
    <control-setting axis="/controls/engines/engine[1]/mixture"  value="1"/>
  </approach>

  <cruise            speed="70" alt="6000"                       fuel="0.8">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1"/>
    <control-setting axis="/controls/engines/engine[1]/throttle" value="1"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="1"/>
    <control-setting axis="/controls/engines/engine[1]/mixture"  value="1"/>
  </cruise>

  <cockpit x="4.608" y="0.270" z="0.585"/>

  <!-- Fuselage -->
  <fuselage ax=" 6.193" ay=" 0.000" az="-0.073" bx=" 5.017" by=" 0.000" bz="-0.059" width="1.253" taper="0.60" midpoint="1"/>
  <fuselage ax=" 5.017" ay=" 0.000" az="-0.059" bx=" 1.464" by=" 0.000" bz="-0.129" width="1.253" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.464" ay=" 0.000" az="-0.129" bx="-0.707" by=" 0.000" bz="-0.063" width="1.253" taper="0.85" midpoint="0"/>
  <fuselage ax="-0.707" ay=" 0.000" az="-0.063" bx="-5.587" by=" 0.000" bz=" 0.239" width="1.064" taper="0.15" midpoint="0"/>
  <fuselage ax="-0.707" ay=" 0.000" az="-0.063" bx="-5.587" by=" 0.000" bz=" 0.068" width="1.064" taper="0.15" midpoint="0"/>

  <!-- Left engine -->
  <fuselage ax=" 4.191" ay=" 2.154" az=" 0.060" bx=" 4.008" by=" 2.154" bz=" 0.060" width="0.868" taper="0.80" midpoint="1"/>
  <fuselage ax=" 4.008" ay=" 2.154" az=" 0.060" bx=" 2.308" by=" 2.154" bz=" 0.060" width="0.868" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.436" ay=" 2.154" az=" 0.049" bx=" 1.932" by=" 2.154" bz=" 0.235" width="0.868" taper="0.20" midpoint="0"/>
  <fuselage ax=" 4.191" ay=" 2.154" az=" 0.560" bx=" 4.008" by=" 2.154" bz=" 0.560" width="0.868" taper="0.80" midpoint="1"/>
  <fuselage ax=" 4.008" ay=" 2.154" az=" 0.560" bx=" 2.308" by=" 2.154" bz=" 0.560" width="0.868" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.590" ay=" 2.154" az=" 0.658" bx=" 1.932" by=" 2.154" bz=" 0.235" width="0.868" taper="0.20" midpoint="0"/>

  <!-- Left engine -->
  <fuselage ax=" 4.191" ay="-2.154" az=" 0.060" bx=" 4.008" by="-2.154" bz=" 0.060" width="0.868" taper="0.80" midpoint="1"/>
  <fuselage ax=" 4.008" ay="-2.154" az=" 0.060" bx=" 2.308" by="-2.154" bz=" 0.060" width="0.868" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.436" ay="-2.154" az=" 0.049" bx=" 1.932" by="-2.154" bz=" 0.235" width="0.868" taper="0.20" midpoint="0"/>
  <fuselage ax=" 4.191" ay="-2.154" az=" 0.560" bx=" 4.008" by="-2.154" bz=" 0.560" width="0.868" taper="0.80" midpoint="1"/>
  <fuselage ax=" 4.008" ay="-2.154" az=" 0.560" bx=" 2.308" by="-2.154" bz=" 0.560" width="0.868" taper="1.00" midpoint="1"/>
  <fuselage ax=" 2.590" ay="-2.154" az=" 0.658" bx=" 1.932" by="-2.154" bz=" 0.235" width="0.868" taper="0.20" midpoint="0"/>

  <wing x=" 2.952" y="0.000" z=" 1.752"
        chord    = "2.191"
        length   = "11.323"
        camber   = "0.05"
        sweep    = "4"
        dihedral = "2"
        taper    = "1">
        <stall   aoa="20" width="1" peak="1.5"/>
        <flap0 start="0.70" 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" side="left"  prop="/surface-positions/left-aileron-pos-norm"/>
        <control-output control="FLAP0" side="right" prop="/surface-positions/right-aileron-pos-norm"/>
  </wing>

  <wing x=" 2.989" y="0.000" z="-0.699"
        append   = "1"
        chord    = "2.191"
        length   = "11.323"
        sweep    = "4"
        dihedral = "2"
        taper    = "1">
        <stall   aoa="20" width="1" peak="1.5"/>
        <flap0 start="0.70" 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>

  <hstab x="-4.425" y="0.000" z=" 0.329"
         chord  = "2.088"
         length = "2.17"
         sweep  = "18"
         taper  = "0.5">
         <stall   aoa="18" width="1" peak="1.5"/>
         <flap0 start="0"    end="1" lift="1.2" 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="-5.077" y="0.000" z=" 0.215"
         chord  = "2.231"
         length = "2.1"
         sweep  = "20"
         taper  = "0.4">
         <stall   aoa="16" 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/Mercedes_D.IVa

    name               : Mercedes D.IVa
    type               : 6-cylinder, inline piston engine
    power              :    252 hp at 1400 rpm
    Compression        : 4.94:1
    weight             : 498.50 kg (    1099 lb    )
    displacement       :  21.72 L  ( 1324.92 cu in )
  -->
  <!-- Left engine -->
  <propeller x="2.924" y=" 2.154" z="0.305"
             mass         = "1099"
             moment       = "-15"
             radius       = "1.566"
             cruise-power = "240"
             cruise-speed = "70"
             cruise-rpm   = "1400"
             cruise-alt   = "6000"
             contra       = "1">
             <actionpt x="1.726" y=" 2.154" z="0.235"/>
             <piston-engine eng-rpm      = "1400"
                            eng-power    = "252"
                            displacement = "1324.92"
                            compression  = "4.94">
                            <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>

  <!-- Right engine -->
  <propeller x="2.924" y="-2.154" z="0.305"
             mass         = "1099"
             moment       = "-15"
             radius       = "1.566"
             cruise-power = "240"
             cruise-speed = "70"
             cruise-rpm   = "1400"
             cruise-alt   = "6000"
             contra       = "1">
             <actionpt x="1.726" y="-2.154" z="0.235"/>
             <piston-engine eng-rpm      = "1400"
                            eng-power    = "252"
                            displacement = "1324.92"
                            compression  = "4.94">
                            <control-input control="THROTTLE" axis="/controls/engines/engine[1]/throttle"/>
                            <control-input control="STARTER"  axis="/controls/engines/engine[1]/starter"/>
                            <control-input control="MAGNETOS" axis="/controls/engines/engine[1]/magnetos"/>
                            <control-input control="MIXTURE"  axis="/controls/engines/engine[1]/mixture"/>
             </piston-engine>
  </propeller>

  <!-- Roues gauches -->
  <gear x="3.227" y=" 2.168" z="-2.238"
        compression = "0.1"
        spring      = "4"
        damp        = "2"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-left"/>
  </gear>

  <!-- Roues droites -->
  <gear x="3.227" y="-2.168" z="-2.238"
        compression = "0.1"
        spring      = "4"
        damp        = "2"
        stiction    = "1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-right"/>
  </gear>

  <!-- Patte de queue gauche 3 -->
  <gear x="-4.468" y=" 0.000" z="-0.586"
        compression = "0.1"
        spring      = "2"
        damp        = "1"
        stiction    = "1">
  </gear>

  <tank x="2.945" y="0.170" z="0.006" capacity="1240"/>

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 2.191 / 6     = 0.365
                 2.952 + 0.365 = 3.317   - 2.788 yet
  -->
  <ballast x="5.900" y="0.000" z="-0.300" mass="900"/>

</airplane>
