<!--This configuration desscibes the A4F as modifified for use by the "Blue Angels"

Initially, eight A-4Fs were specially reconfigured for Blue Angel use.  
Refinements inclued removal of the "humpback" avionics pod; 
a drag chute; control stick "load feel" bungees; 
a smoke generation system; an inverted flight fuel system; 
alteration of the horizontal stabilizer trim; permanent closure of the wing slats; 
and a self-contained, foldable cockpit access ladder.

The data are as accurate as I can make them, and provide a reasonable flight model

Author - Vivian Meazza

-->

<airplane mass="10448">

  <!-- Approach configuration -->
  <approach speed="150" aoa="15" fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.4"/>
    <control-setting axis="/controls/flight/flaps" value="1.0"/>
    <control-setting axis="/controls/gear/gear-down" value="1"/>
    <control-setting axis="/controls/flight/speedbrake" value="1"/>
    <solve-weight idx="0" weight="200"/>
    <!--	<solve-weight idx="1" weight="0" />-->
  </approach>

  <!-- Cruise configuration.  This number is for an A-4F (595mph/FL340) -->
  <cruise speed="584" alt="34000" fuel="0.5">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="1"/>
    <control-setting axis="/controls/flight/flaps" value="0.0"/>
    <control-setting axis="/controls/gear/gear-down" value="0"/>
    <solve-weight idx="0" weight="200"/>
    <!--	<solve-weight idx="1" weight="0" />-->
  </cruise>

  <cockpit x="2.76" y="0.0" z="0.9"/>

  <fuselage ax="5.61" ay="0" az="-0.25" 
            bx="-6.59" by="0" bz="0"
            width="1.70" taper="0.5" midpoint="0.3"/>

  <wing x="-0.38" y=".71" z="-0.38" 
        taper="0.15"
        incidence="2.5" 
        twist="-2.5"
        length="3.855" 
        chord="4.07" 
        sweep="28" 
        dihedral="1" 
        camber="0.04"
        effectiveness="1.0">
    <stall aoa="27" width="10" peak="1.3"/>
    <flap0 start="0.0" end="0.5" lift="1.3" drag="1.3"/>
    <flap1 start="0.5" end="1.0" lift="1.2" drag="1.2"/>
    <spoiler start="0.0" end="0.5" lift="0.0" drag="1.5"/>
    <control-input axis="/controls/flight/flaps" control="FLAP0"/>
    <control-input axis="/controls/flight/spoiler" control="SPOILER"/>
    <control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
    <control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
    <control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
    <control-output control="SPOILER" prop="/surface-positions/spoiler-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"/>
    <control-speed control="FLAP1" transition-time="1"/>
    <control-speed control="SPOILER" transition-time="2"/>
  </wing>

  <hstab x="-5.27" y="0.01" z="0.93" 
         taper="0.170"
         effectiveness="2.0"
         length="1.863"
         chord="2.00"
         sweep="28">
    <stall aoa="27" width="10" peak="1.5"/>
    <flap0 start="0" end="1" lift="1.6" drag="1.2"/>
    <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"/>
    <control-speed control="FLAP0" transition-time="1"/>
  </hstab>

  <!--<vstab x="-4.35" y="0" z="0.93" taper=".176"
       length="2.648" chord="3.87" sweep="45" effectiveness="1.0">
-->
  <vstab x="-4.85" y="0" z="0.88" 
         taper="0.24"
         length="2.354" 
         chord="2.89" 
         sweep="35" 
         effectiveness="1.0">
    <stall aoa="27" width="10" peak="1.5"/>
    <flap0 start="0" end="1" lift="1.3" drag="1.2"/>
    <control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
    <control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
    <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"
                   min="1" max="-1"/>
    <control-speed control="FLAP0" transition-time="0.5"/>
    <flap1 start="-0.6" end="-0.75" lift="1" drag="6"/>
    <control-input axis="/controls/flight/speedbrake" control="FLAP1" />
    <control-output control="FLAP1"  prop="/surface-positions/speedbrake-pos-norm"/>
    <control-speed control="FLAP1" transition-time="2.5"/>
  </vstab>

  <!-- dummy vstab to provide drag-chute -->
  <vstab x="-6.0" y="0.0" z="0.26"
         taper="1"
         incidence="0"
         twist="0"
         length="0.5"
         chord="0.25"
         sweep="0"
         dihedral="90"
         effectiveness="1" >
    <stall aoa="27" width="3" peak="1.3"/>
    <flap0 start="0" end="1.0" lift="1" drag="30"/>
    <control-input axis="/controls/flight/drag-chute/lever" control="FLAP0"/>
    <control-output control="FLAP0" prop="/surface-positions/drag-chute-pos-norm"/>
    <control-speed control="FLAP0" transition-time="2"/>
  </vstab>

  <!-- 11,200 lb thrust Pratt & Whitney J52-P408 engine. -->
  <jet x="0.75" y="0" z="-0.15" 
       mass="2500" thrust="11200" n1-max="106"
       exhaust-speed="2000">
    <actionpt x="0.61" y="0" z="0"/>
    <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
  </jet>

  <!-- nose   -->
  <gear x="3.32" y="0" z="-2.25" 
        retract-time="7" 
        compression="0.7" 
        castering="0"
        damper="3"
        spring="0.8"
        sfric="1" dfric="0.8">
    <control-input axis	="/controls/flight/rudder" control="STEER" square="false"
                   src0="-1" src1="1" dst0="-0.75" dst1="0.75"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
    <control-output control="STEER" prop="/gear/gear[0]/steering-norm"/>
    <control-speed control="EXTEND" transition-time="7"/>
  </gear>

  <!-- left main 	-->
  <gear x="-0.78" y="1.19" z="-1.99" 
        retract-time="7" 
        compression="0.75"
        spring="0.8"
        damper="3"
        sfric="1" dfric="0.8">
    <control-input axis="/controls/gear/brake-left" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
    <control-speed control="EXTEND" transition-time="7"/>
  </gear>

  <!-- right main -->
  <gear x="-0.78" y="-1.19" z="-1.99"
        retract-time="7"
        compression="0.75"
        spring="0.8" 
        damper="3"
        sfric="1" dfric="0.8">
    <control-input axis="/controls/gear/brake-right" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
    <control-speed control="EXTEND" transition-time="7"/>
  </gear>

  <!-- Hook -->
  <hook x="-3.12" y="0.0" z="-0.70" 
        length="1.94" 
        down-angle="80" 
        up-angle="-5">
    <control-input axis="/controls/gear/tailhook" control="HEXTEND"/>
    <control-speed control="HEXTEND" transition-time="4"/>
  </hook>

  <!-- Launch-bar -->
  <launchbar 	x="0.44" y="0.0" z="-0.54" 
        length="2.29" 
        down-angle="90"
        up-angle="0"
        holdback-x="-3.12" holdback-y="0.0" holdback-z="-0.70" holdback-length="7.5">
    <control-input axis="/controls/gear/launchbar" control="LEXTEND"/>
    <control-speed control="LEXTEND" transition-time="1"/>
  </launchbar>

  <!-- A4-M had 800 gallons of in-fuselage fuel capacity in three tanks,
     one in each wing and one behind the cockpit. TA-4F had "only" 100
     gallons in the fuselage due to the second seat, so the wings must
     have 0-350 gallons each.  Call the tanks 260/280/260 gallons, and
     use 6.72 lbs/gal for Jet-A fuel. BUT: this is an A-4E, which had
     770 gallons.  Figure that the extra 30 all went into an expanded
     center tank underneath the new "hump" in the fuselage. -->
  <tank x="0.11" y="0" z="-0.10"
        jet="true"
        capacity="1678"/>
  <tank x="-0.310" y="1.0" z="-0.4"
        jet="true"
        capacity="1750"/>
  <tank x="-0.310" y="-1.0" z="-0.4"
        jet="true"
        capacity="1750"/>

  <!--  Ballast and Weights -->
  <ballast x="4.49" y="0" z="-0.55" mass="1600"/>
  <!-- cockpit -->

  <!-- The early A-4's had five pylons.  One 3500lbs center for a tank,
     two inboard pylons holding 2250lbs, and two 1000lbs outboard
     pylons. 
<weight x="-1.39" y="3" z="-1.33" size="1" 
        mass-prop="/sim/weight[0]/weight-lb"/>
<weight x="-0.79" y="2" z="-1.33" size="1" 
        mass-prop="/sim/weight[1]/weight-lb"/>
<weight x="-0.39" y="0" z="-1.33" size="1.5" 
        mass-prop="/sim/weight[2]/weight-lb"/>
<weight x="-0.79" y="-2" z="-1.33" size="1" 
        mass-prop="/sim/weight[3]/weight-lb"/>
<weight x="-1.39" y="-3" z="-1.33" size="1" 
        mass-prop="/sim/weight[4]/weight-lb"/>-->
  <weight x="2.76" y="0" z="-0.04" mass-prop="/yasim/weights/pilot-lb"/>
  <!-- <weight x="-6.03" y="0" z="0.22" mass-prop="/yasim/weights/drag-chute" size="2"/>-->

</airplane>
