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

<!-- Convair F 106 Delta Dart :    2009 BARANGER Emmanuel
                      updated :    2013 BARANGER Emmanuel
                      updated : 08/2024 BARANGER Emmanuel

     Source       : http://en.wikipedia.org/wiki/F-106_Delta_Dart

     Wingspan     : 11.67 m  ( 38.25 ft )
     Length       : 21.55 m  ( 70.70 ft )
     Height       :  6.18 m  ( 20.28 ft )
     Empty weight : 11077 kg ( 24420 lb )
     Gross weight : 15653 kg ( 34510 lb )
     Moteur       : Pratt & Whitney J75-17 afterburning  turbojet, 24500 lbf.
     Speed max    : Mach 2.3 ( 2455 km/h / 1325.59 kts )
     Reservoirs
       Internes   : 2 x 4921.5 lb
       Externes   : 2 x 2325.5 lb
-->
<airplane mass="24420" version="YASIM_VERSION_CURRENT" mtow-lbs="34510">

  <!-- Approach configuration -->
  <approach          speed="120" aoa="2"                            fuel="0.3">
    <control-setting axis="/controls/engines/engine[0]/throttle"    value="0.3"/>
    <control-setting axis="/controls/engines/engine[0]/afterburner" value="0"/>
    <control-setting axis="/controls/flight/flaps"                  value="0.3"/>
    <control-setting axis="/controls/gear/gear-down"                value="1"/>
    <control-setting axis="/controls/flight/speedbrake"             value="0"/>
    <control-setting axis="/controls/flight/slats"                  value="1"/>
  </approach>

  <!-- Cruise configuration.   -->
  <cruise            speed="1200" alt="45000"                       fuel="0.8">
    <control-setting axis="/controls/engines/engine[0]/throttle"    value="1"/>
    <control-setting axis="/controls/engines/engine[0]/afterburner" value="0"/>
    <control-setting axis="/controls/flight/flaps"                  value="0"/>
    <control-setting axis="/controls/gear/gear-down"                value="0"/>
    <control-setting axis="/controls/flight/speedbrake"             value="0"/>
    <control-setting axis="/controls/flight/slats"                  value="0"/>
  </cruise>

  <!-- pilot eyepoint -->
  <cockpit x="4.197" y="0" z="-0.150"/>

  <fuselage ax=" 6.177" ay=" 0.000" az="-0.793" bx="  4.683" by=" 0.000" bz="-0.520" width="1.539" taper="0.20" midpoint="1"/>
  <fuselage ax=" 4.814" ay=" 0.000" az="-0.518" bx=" -7.015" by=" 0.000" bz="-0.518" width="1.539" taper="1.00" midpoint="1"/>

  <fuselage ax=" 9.270" ay=" 0.000" az="-1.473" bx="  8.657" by=" 0.000" bz="-1.418" width="0.420" taper="0.10" midpoint="1"/>
  <fuselage ax=" 8.657" ay=" 0.000" az="-1.418" bx="  7.806" by=" 0.000" bz="-1.382" width="0.784" taper="0.54" midpoint="1"/>
  <fuselage ax=" 7.806" ay=" 0.000" az="-1.382" bx="  6.462" by=" 0.000" bz="-1.272" width="1.191" taper="0.66" midpoint="1"/>
  <fuselage ax=" 6.462" ay=" 0.000" az="-1.272" bx="  4.946" by=" 0.000" bz="-1.162" width="1.407" taper="0.85" midpoint="1"/>
  <fuselage ax=" 4.946" ay=" 0.000" az="-1.162" bx="  2.502" by=" 0.000" bz="-1.056" width="1.539" taper="0.92" midpoint="1"/>
  <fuselage ax=" 2.502" ay=" 0.000" az="-1.056" bx=" -3.696" by=" 0.000" bz="-0.887" width="1.539" taper="1.00" midpoint="1"/>
  <fuselage ax="-3.696" ay=" 0.000" az="-0.887" bx=" -7.008" by=" 0.000" bz="-0.631" width="1.798" taper="0.86" midpoint="1"/>
  <fuselage ax="-7.008" ay=" 0.000" az="-0.631" bx=" -8.299" by=" 0.000" bz="-0.631" width="1.798" taper="1.00" midpoint="1"/>
  <fuselage ax="-8.299" ay=" 0.000" az="-0.631" bx="-10.018" by=" 0.000" bz="-0.391" width="1.798" taper="0.70" midpoint="0"/>

  <!-- Left reservoir -->
  <fuselage ax="-0.282" ay=" 2.662" az="-1.986" bx=" -0.634" by=" 2.662" bz="-1.967" width="0.351" taper="0.10" midpoint="1"/>
  <fuselage ax="-0.634" ay=" 2.662" az="-1.967" bx=" -1.140" by=" 2.662" bz="-1.943" width="0.507" taper="0.70" midpoint="1"/>
  <fuselage ax="-1.140" ay=" 2.662" az="-1.943" bx=" -1.868" by=" 2.662" bz="-1.906" width="0.607" taper="0.84" midpoint="1"/>
  <fuselage ax="-1.868" ay=" 2.662" az="-1.906" bx=" -5.265" by=" 2.662" bz="-1.747" width="0.607" taper="1.00" midpoint="1"/>
  <fuselage ax="-5.265" ay=" 2.662" az="-1.747" bx=" -6.133" by=" 2.662" bz="-1.703" width="0.607" taper="0.75" midpoint="0"/>
  <fuselage ax="-6.133" ay=" 2.662" az="-1.703" bx=" -7.128" by=" 2.662" bz="-1.652" width="0.455" taper="0.05" midpoint="0"/>

  <!-- Right reservoir -->
  <fuselage ax="-0.282" ay="-2.662" az="-1.986" bx=" -0.634" by="-2.662" bz="-1.967" width="0.351" taper="0.10" midpoint="1"/>
  <fuselage ax="-0.634" ay="-2.662" az="-1.967" bx=" -1.140" by="-2.662" bz="-1.943" width="0.507" taper="0.70" midpoint="1"/>
  <fuselage ax="-1.140" ay="-2.662" az="-1.943" bx=" -1.868" by="-2.662" bz="-1.906" width="0.607" taper="0.84" midpoint="1"/>
  <fuselage ax="-1.868" ay="-2.662" az="-1.906" bx=" -5.265" by="-2.662" bz="-1.747" width="0.607" taper="1.00" midpoint="1"/>
  <fuselage ax="-5.265" ay="-2.662" az="-1.747" bx=" -6.133" by="-2.662" bz="-1.703" width="0.607" taper="0.75" midpoint="0"/>
  <fuselage ax="-6.133" ay="-2.662" az="-1.703" bx=" -7.128" by="-2.662" bz="-1.652" width="0.455" taper="0.05" midpoint="0"/>

  <wing x="-2.596" y="0" z="-1.129"
        chord    = "11.313"
        length   = "7.5"
        taper    = "0.035"
        sweep    = "39.5"
        dihedral = "-3"
        camber   = "0.001">
        <stall     aoa="14" width="1"    peak="1.5"/>
        <flap0   start="0.16" end="0.48" lift="1.2" drag="1.3"/>
        <flap1   start="0.48" end="0.83" lift="1.8" drag="1.2"/>
        <spoiler start="0.48" end="0.83" lift="2.3" drag="13"/>

        <control-input  control="FLAP0"   axis="/controls/flight/flaps"        invert="true"/>
        <control-input  control="FLAP1"   axis="/controls/flight/aileron"      split="true"/>
        <control-input  control="FLAP1"   axis="/controls/flight/aileron-trim" split="true"/>
        <control-input  control="SPOILER" axis="/controls/flight/spoilers"/>

        <control-output control="FLAP0"   prop="/surface-positions/slat-pos-norm"/>
        <control-output control="FLAP1"   prop="/surface-positions/flap-pos-norm"/>
        <control-output control="SPOILER" prop="/surface-positions/speedbrake-pos-norm"/>

        <control-speed  control="FLAP0"   transition-time="1.1"/>
        <control-speed  control="SPOILER" transition-time="1.5"/>
  </wing>

  <hstab x="-2.596" y="0" z="-1.129"
         chord    = "11.313"
         length   = "7.5"
         taper    = "0.035"
         sweep    = "39.5"
         dihedral = "-3">
         <stall   aoa="14" width="1"    peak="1.5"/>
         <flap0 start="0.16" end="0.83" 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="-7.486" y="0.0" z="0.141"
         chord  = "4.998"
         length = "4.1"
         taper  = "0.28"
         sweep  = "40">
         <stall   aoa="14" width="1"    peak="1.5"/>
         <flap0 start="0.2"  end="0.72" 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"/>
  </vstab>

  <!-- Pratt & Whitney J75 axial-flow

       Engines   source            : http://en.wikipedia.org/wiki/Pratt_%26_Whitney_J75

                 name              : Pratt & Whitney J75-P-17
                 type              : Turbojet afterburning thrust
                 Weight            : 5020 lb (2277 kg)
                 thrust            : 17200 lb
                 afterburner       : 24500 lb
  -->
  <jet x="-2.688" y="0.0" z="-0.749"
       mass        = "5020"
       thrust      = "17200"
       afterburner = "24500"
       n1-idle     = "30"
       n1-max      = "100"
       n2-idle     = "55"
       n2-max      = "100"
       tsfc        = "0.79">
       <actionpt x="-10.202" y="0.0" z="-0.429"/>
       <control-input  control="THROTTLE" axis="/controls/engines/engine[0]/throttle"/>
       <control-input  control="REHEAT"   axis="/controls/engines/engine[0]/throttle" src0="0.85" src1="1.0" dst0="0.0" dst1="1.0"/>

       <control-output control="REHEAT"   prop="engines/engine[0]/afterburner" />

       <control-speed  control="THROTTLE" transition-time="2"/>
       <control-speed  control="REHEAT"   transition-time="2"/>
  </jet>

  <!-- gear -->
  <!-- nose -->
  <gear x="4.028" y="0.000" z="-3.063"
        compression = "0.44"
        spring      = "1.1"
        stiction    = "1">
        <control-input  control="STEER"  axis="/controls/flight/rudder" square="false"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="7"/>
  </gear>

  <!-- left main -->
  <gear x="-3.323" y="2.169" z="-3.062"
        compression = "0.72"
        spring      = "1"
        stiction    = "1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-left"/>
        <control-input  control="BRAKE"  axis="/controls/gear/brake-parking"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="7"/>
  </gear>

  <!-- right main -->
  <gear x="-3.323" y="-2.169" z="-3.062"
        compression = "0.72"
        spring      = "1"
        stiction    = "1">
        <control-input  control="BRAKE"  axis="/controls/gear/brake-right"/>
        <control-input  control="BRAKE"  axis="/controls/gear/brake-parking"/>
        <control-input  control="EXTEND" axis="/controls/gear/gear-down"/>

        <control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>

        <control-speed  control="EXTEND" transition-time="7"/>
  </gear>

  <!-- Internal Tanks weight total : 4465 kg -> 9843 lb -> 2 x 4921.5 -> 1300 Gal US -->
  <tank x="-2.4" y=" 2.3" z="-1.237" jet="true" capacity="4921.5"/>
  <tank x="-2.4" y="-2.3" z="-1.237" jet="true" capacity="4921.5"/>

  <!-- External Tanks weight total : 2110 kg -> 4651 lb -> 2 x 2325.5 -> 614 Gal US -->
  <tank x="-3.627" y=" 2.658" z="-1.817" jet="true" capacity="2325.5"/>
  <tank x="-3.627" y="-2.658" z="-1.817" jet="true" capacity="2325.5"/>

  <!-- Mass distribution -->
  <ballast x="8.5" y="0" z="-1.4" mass="1500"/>

</airplane>
