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

<!-- Ansaldo SVA 5    : BARANGER Emmanuel 10/2014

     sources          : https://www.wikiwand.com/en/articles/Ansaldo_SVA

     wingspan         :  9.10 m    (   29 ft 10 in )
     length           :  8.10 m    (   26 ft  7 in )
     height           :  2.65 m    (    8 ft  8 in )
     empty weight     :   680 kg   ( 1499 lb       )
     Gross weight     :  1050 kg   ( 2315 lb       )
     engine           : 1 SPA 6A 6-cylinder water-cooled in-line piston engine ( 200 hp )
     max speed        :   230 km/h (  120 kn       )
-->
<airplane mass="1499" version="YASIM_VERSION_CURRENT" mtow-lbs="2315">

  <!-- Approach configuration -->
  <approach speed="37" aoa="2" fuel="0.3">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.15"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="1"/>
  </approach>

  <!-- Cruise configuration -->
  <cruise speed="110" alt="5000" fuel="0.8">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/mixture"  value="1"/>
  </cruise>

  <!-- pilot eyepoint -->
  <cockpit x="0.689" y="0" z="0.941"/>

  <fuselage ax=" 3.728" ay=" 0.000" az=" 0.204" bx=" 3.653" by=" 0.000" bz=" 0.204" width="0.357" taper="0.40" midpoint="1"/>
  <fuselage ax=" 3.653" ay=" 0.000" az=" 0.204" bx=" 3.516" by=" 0.000" bz=" 0.204" width="0.517" taper="0.70" midpoint="1"/>
  <fuselage ax=" 3.516" ay=" 0.000" az=" 0.204" bx=" 3.252" by=" 0.000" bz=" 0.204" width="0.693" taper="0.75" midpoint="1"/>
  <fuselage ax=" 3.252" ay=" 0.000" az=" 0.204" bx=" 2.843" by=" 0.000" bz=" 0.204" width="0.860" taper="0.81" midpoint="1"/>
  <fuselage ax=" 2.843" ay=" 0.000" az=" 0.204" bx=" 2.199" by=" 0.000" bz=" 0.204" width="0.950" taper="0.90" midpoint="1"/>
  <fuselage ax=" 2.199" ay=" 0.000" az=" 0.204" bx=" 1.220" by=" 0.000" bz=" 0.204" width="0.950" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.220" ay=" 0.000" az=" 0.204" bx="-3.247" by=" 0.000" bz=" 0.204" width="0.950" taper="0.10" midpoint="0"/>

  <fuselage ax=" 2.836" ay=" 0.000" az=" 0.154" bx=" 2.198" by=" 0.000" bz=" 0.066" width="0.950" taper="0.90" midpoint="1"/>
  <fuselage ax=" 2.198" ay=" 0.000" az=" 0.066" bx=" 1.220" by=" 0.000" bz=" 0.039" width="0.950" taper="1.00" midpoint="1"/>
  <fuselage ax=" 1.220" ay=" 0.000" az=" 0.039" bx="-3.247" by=" 0.000" bz=" 0.039" width="0.950" taper="0.10" midpoint="0"/>

  <!-- upper wing -->
  <wing x="1.888" y="0" z="1.293"
        chord="1.968"
        length="4.556"
        taper="1"
        incidence="3"
        camber="0.12">
        <stall   aoa="20" width="13" peak="1.5"/>
        <flap1 start="0.47" 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>

  <!-- lower wing -->
  <mstab x="1.981" y="0" z="-0.309"
         chord="1.762"
         length="3.709"
         dihedral="2.5"
         taper="1"
         incidence="3"
         camber="0.12">
         <stall aoa="20" width="1" peak="1.5"/>
  </mstab>

  <!-- tailplane -->
  <hstab x="-3.358" y="0" z="0.282"
         chord="1.333"
         length="1.6"
         incidence="0.25"
         sweep="15"
         taper="0.4"
         camber="0.012">
         <stall   aoa="18" width="1" peak="1.0"/>
         <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>

  <!-- tail -->
  <vstab x="-2.864" y="0" z="-0.005"
         chord="2.369"
         length="1.70"
         sweep="33"
         taper="0.24">
         <stall   aoa="16" width="1" peak="1.0"/>
         <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            : https://www.wikiwand.com/en/articles/SPA_6A

                 name              : SPA 6A
                 type              : Inline six-cylinder piston engine
                 power             :   150 hp at 1600 rpm (rated). 200 hp at 1600 rpm (maximum).
                 weight            :   255 kg (   562 lb)
                 displacement      : 14.57 L  ( 888.9 cu in)
  -->
  <propeller x="3.280" y="0" z="0.324"
             mass="474"
             moment="16"
             radius="1.55"
             cruise-alt="2000"
             cruise-speed="110"
             cruise-rpm="1600"
             cruise-power="150"
             takeoff-power="200"
             takeoff-rpm="1600">
             <actionpt x="3.952" y="0" z="0.324"/>
             <piston-engine eng-power="200"
                            eng-rpm="1600"
                            displacement="8880.9">
                            <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 main -->
  <gear x="2.741" y=" 0.913" z="-1.503"
        compression="0.15"
        spring="2"
        damp="2"
        stiction="1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
        <control-input control="STEER" axis="/sim/gears/toe-left"/>
  </gear>

  <!-- right main -->
  <gear x="2.741" y="-0.913" z="-1.503"
        compression="0.15"
        spring="2"
        damp="2"
        stiction="1">
        <control-input control="BRAKE" axis="/controls/gear/brake-parking" split="true"/>
        <control-input control="STEER" axis="/sim/gears/toe-right"/>
  </gear>

  <!-- Tail skid -->
  <gear x="-3.026" y="0" z="-0.383"
        compression="0.05"
        spring="1"
        damp="2"
        stiction="1">
  </gear>

  <!-- fuel -->
  <tank x="1.565" y="0" z="-0.205" capacity="200"/>

  <!-- Mass distribution
       Dilbert : The cg should be about 1/6 chord ahead of the chord center.
                 1.968 / 6     = 0.328
                 1.888 + 0.328 = 2.216
  -->
  <ballast x="3.4" y="0" z="0.1" mass="225"/>

</airplane>
