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

<!-- Coanda 1910      : 2013 Emmanuel BARANGER

     sources          : http://www.militaryfactory.com/aircraft/detail.asp?aircraft_id=682
                      : http://en.wikipedia.org/wiki/Coand%C4%83-1910

     wingspan         : 10.3 m     ( 33 ft 10 in    )
     length           : 12.5 m     ( 41 ft 01 in     )
     height           :  2.90 m    (  9 ft 5 1/3 in )
     weight           :   420 kg   ( 920 lb         )
     engine           : 1 x Four-cylinder inline water-cooled engine developing (50 hp) at 1000 rpm driving a compressor for 450 lbf thrust
     Cruise speed     :   150 km/h ( 81 kts )
     Maximum speed    :   180 km/h ( 97 kts )
-->

<airplane mass="920" version="YASIM_VERSION_CURRENT">

  <!-- Approach configuration -->
  <approach speed="30" aoa="4" fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.6"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise speed="81" alt="6000" fuel="0.5">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.7"/>
  </cruise>

  <cockpit x="0.42143" y="0" z="0.91679"/>

  <fuselage ax="6.24844" ay="0" az="0.34787" bx="-5.55058" by="0" bz="0.36783" width="0.44" taper="0.3" midpoint="0.3"/>

  <!-- Wing up -->
  <wing x="2.48992" y="0" z="1.49834"
        chord="2.046" 
        length="4.745" 
        taper="1"
        camber="0.01">
        <stall aoa="18" width="1" peak="1.5"/>
        <flap1 start="0.63" end="0.97" lift="1.2" drag="1.1"/>

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

        <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-output control="FLAP1" prop="/surface-positions/aileron-pos-norm"/>
  </wing>

  <!-- Wing down -->
  <mstab x="2.48992" y="0" z="-0.98166"
         chord="2.046" 
         length="2.921" 
         taper="1"
         camber="0.01">
         <stall aoa="18" width="1" peak="1.5"/>
  </mstab>

  <!-- Rear wing -->
  <mstab x="-2.82732" y="0" z="0.07386"
         chord="1.011" 
         length="1.039" 
         taper="1"
         camber="0.01">
         <stall aoa="18" width="1" peak="1.5"/>
  </mstab>

  <hstab x="-4.75266" y="0" z="0.37895"
         chord="2.968" 
         length="1.36" 
         taper="0.2"
         sweep="62">
         <stall aoa="14" width="1" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.4" drag="1.1"/>

         <control-input axis="/controls/flight/elevator" control="FLAP0"/>
         <control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>

         <control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
  </hstab>

  <vstab x="-4.75266" y="0" z="0.37895"
         chord="2.968"
         length="1.36"
         taper="0.2"
         sweep="62">
         <stall aoa="14" width="3" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.2" drag="1.2"/>

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

         <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm" min="1" max="-1"/>
  </vstab>

  <vstab x="-4.75266" y="0" z="0.37895"
         chord="2.968"
         length="1.36"
         taper="0.2"
         dihedral="270"
         sweep="62">
         <stall aoa="14" width="3" peak="1.5"/>
         <flap0 start="0" end="1" lift="1.2" drag="1.2"/>

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

  <!-- Engines   source            : ?

                 type              : Motorjet
  -->
  <jet x="5.37976" y="0" z="0.34787"
       thrust="450"
       mass="200"
       n1-idle="30"
       n1-max="90" 
       n2-idle="35"
       n2-max="95"
       egt="850" 
       tsfc="1.39">
       <actionpt x="4.51440" y="0" z="0.34787"/>
       <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
  </jet>
  
  <!-- Left wheel -->
  <gear x="2.94734" y="0.87472" z="-1.65062"
        compression="0.02" 
        spring="1.8" 
        damp="0.03" 
        on-solid="1" >
  </gear>

  <!-- Right wheel -->
  <gear x="2.94734" y="-0.87472" z="-1.65062"
        compression="0.02" 
        spring="1.8"
        damp="0.03" 
        on-solid="1" >
  </gear>

  <!-- Noze wheel -->
  <gear x="-4.73351" y="0" z="-0.52823" 
        compression="0.15" 
        spring="0.8"
        on-solid="1"
        sfric="1"
        dfric="1">
  </gear>

  <!-- Noze contact point 1 -->
  <gear x="4.91202" y="0" z="-1.44908"
        compression="0.01">
  </gear>

  <!-- Noze contact point 2 -->
  <gear x="4.68623" y="0" z="-1.59679"
        compression="0.01">
  </gear>

  <tank x="2.98131" y="0" z="0.58940" capacity="56" />

 <!-- Mass distribution -->
  <ballast x="6" y="0" z="-1" mass="200"/>

</airplane>
