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

<!--  Fokker S 11 - Emmanuel BARANGER -    2019
           Update - Emmanuel BARANGER - 03/2021
           Update - Emmanuel BARANGER - 03/2025

  sources      : http://en.wikipedia.org/wiki/Fokker_S-11

  Wingspan     : 11.00 m     (   36 ft 1 in )
  lenght       :  8.18 m     (   26 ft 8 in )
  height       :  2.22 m     (    7 ft 5 in )
  Empty mass   :   810 kg    ( 1784 lb      )
  Gross weight :  1100 kg    ( 2425 lb      )
  Engine       : 1 Lycoming O-435A ( 190 hp )
  Cruise speed :   164 km/h  (   89 kts     )
  Maximum speed:   209 km/h  (  113 kts     )
-->
<airplane mass="1784" version="YASIM_VERSION_CURRENT" mtow-lbs="2425">

  <!-- Approach configuration -->
  <approach speed="58" aoa="2" fuel="0.3">
    <control-setting axis="/controls/engines/engine[0]/throttle"        value="0.2"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"         value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0"/>
    <control-setting axis="/controls/flight/flaps"                      value="1"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise speed="89" alt="5000" fuel="1.0">
    <control-setting axis="/controls/engines/engine[0]/throttle"        value="1"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"         value="1"/>
    <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="1"/>
    <control-setting axis="/controls/flight/flaps"                      value="0"/>
  </cruise>

  <cockpit x="1.55" y="0.31" z="0.547"/>

  <!-- Casserole -->
  <fuselage ax="4.095" ay=" 0.000" az=" 0.015" bx=" 3.960" by=" 0.000" bz=" 0.015" width="0.264" taper="0.20" midpoint="1"/>
  <fuselage ax="3.960" ay=" 0.000" az=" 0.015" bx=" 3.792" by=" 0.000" bz=" 0.015" width="0.322" taper="0.82" midpoint="1"/>

  <!-- Fuselage -->
  <fuselage ax="3.793" ay=" 0.230" az=" 0.000" bx=" 1.820" by=" 0.000" bz=" 0.000" width="1.279" taper="0.40" midpoint="1"/>
  <fuselage ax="3.793" ay="-0.230" az=" 0.000" bx=" 1.820" by=" 0.000" bz=" 0.000" width="1.279" taper="0.40" midpoint="1"/>

  <fuselage ax="3.785" ay=" 0.230" az="-0.241" bx=" 1.820" by=" 0.000" bz="-0.070" width="1.279" taper="0.40" midpoint="1"/>
  <fuselage ax="3.785" ay="-0.230" az="-0.241" bx=" 1.820" by=" 0.000" bz="-0.070" width="1.279" taper="0.40" midpoint="1"/>

  <fuselage ax="1.820" ay=" 0.000" az=" 0.000" bx=" 0.058" by=" 0.000" bz=" 0.000" width="1.279" taper="1.00" midpoint="0"/>
  <fuselage ax="0.058" ay=" 0.000" az=" 0.000" bx="-4.080" by=" 0.000" bz=" 0.000" width="1.279" taper="0.20" midpoint="0"/>

  <fuselage ax="1.820" ay=" 0.000" az="-0.070" bx=" 0.058" by=" 0.000" bz="-0.070" width="1.279" taper="1.00" midpoint="0"/>
  <fuselage ax="0.058" ay=" 0.000" az="-0.070" bx="-4.080" by=" 0.000" bz=" 0.000" width="1.279" taper="0.20" midpoint="0"/>

  <!-- Cabine -->
  <fuselage ax="2.370" ay=" 0.000" az=" 0.400" bx=" 1.850" by=" 0.000" bz=" 0.400" width="1.089" taper="0.30" midpoint="1"/>
  <fuselage ax="1.850" ay=" 0.000" az=" 0.400" bx=" 0.758" by=" 0.000" bz=" 0.400" width="1.089" taper="1.00" midpoint="0"/>
  <fuselage ax="0.758" ay=" 0.000" az=" 0.400" bx="-0.310" by=" 0.000" bz=" 0.400" width="1.089" taper="0.30" midpoint="0"/>

  <wing x="1.447" y="0" z="-0.569"
        chord="2.315"
        length="1.52"
        taper="0.80"
        camber="0.005"
        sweep="9">
        <stall aoa="20" width="1" peak="1.5"/>
  </wing>

  <wing x="1.211" y="1.501" z="-0.569"
        append="1"
        chord="1.86"
        length="3.967"
        taper="0.72"
        dihedral="7"
        camber="0.005"
        sweep="-2">
        <stall   aoa="20"  width="1"     peak="1.5"/>
        <flap0 start="0.000" end="0.305" lift="1.5" drag="2.8"/>
        <flap1 start="0.305" end="0.890" 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" side="left"  prop="/surface-positions/left-aileron-pos-norm"/>
        <control-output control="FLAP1" side="right" prop="/surface-positions/right-aileron-pos-norm"/>

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

  <hstab x="-3.158" y="0" z="0.328"
         chord="1.134"
         length="1.70"
         taper="0.60"
         sweep="7.5">
         <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="-3.023" y="0" z="0.176"
       chord="2.082"
       length="1.4"
       taper="0.30"
       sweep="15">
       <stall   aoa="16" width="1" peak="1.5"/>
       <flap0 start="0"    end="1" lift="1.3" drag="1.2"/>

       <control-input  control="FLAP0" axis="/controls/flight/rudder" invert="true"/>

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

  <!--  Lycoming O-435A sources      : http://en.wikipedia.org/wiki/Lycoming_O-435

                        Type         : Six-cylinder horizontally-opposed gasoline piston engine
                        weight       : 433 lb (96.6 kg)
                        Max power    : 212 hp at 3000 rpm
                        Weight       : 350 lbs
                        Displacement : 435 in3
                        Compression  : 7.5:1
  -->
  <propeller x="2.920" y="0" z="0.029"
             mass="433"
             radius="1.1"
             moment="6"
             cruise-speed="89"
             cruise-rpm="2600"
             cruise-alt="5000"
             cruise-power="200"
             takeoff-power="212"
             takeoff-rpm="2550" >
             <actionpt x="3.920" y="0" z="0.029" />
             <piston-engine eng-rpm="3000"
                            eng-power="212"
                            displacement="434"
                            compression="7.5">
                            <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"/>
                            <control-input control="MIXTURE"  axis="/controls/engines/engine[0]/mixture" />
             </piston-engine>
  </propeller>

  <gear x="2.110" y="1.429" z="-1.551"
        compression="0.25"
        spring="0.6">
        <control-input control="BRAKE" axis="/controls/gear/brake-left"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <gear x="2.110" y="-1.429" z="-1.551"
        compression="0.25"
        spring="0.6">
        <control-input control="BRAKE" axis="/controls/gear/brake-right"/>
        <control-input control="BRAKE" axis="/controls/gear/brake-parking"/>
  </gear>

  <gear x="-3.197" y="0" z="-0.576"
        compression="0.15"
        spring="0.6">
        <control-input control="STEER" axis="/controls/flight/rudder" square="true" src0="-1" src1="1" dst0="0.25" dst1="-0.25"/>
   </gear>

  <!-- Fuel  -->
  <tank x="0.72" y="0" z="-0.272" capacity="300" />

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 2.315 / 6     = 0.385
                 1.447 + 0.385 = 1.832
  -->
  <ballast x="3" y="0" z="0" mass="496"/>

</airplane>
