<airplane mass="9853">

<!-- Approach configuration -->
<approach speed="130" aoa="13.5">
  <control-setting axis="/controls/throttle[0]" value="0.2"/>
  <control-setting axis="/controls/flaps" value="1.0"/>
  <control-setting axis="/controls/gear-down" value="1"/>
</approach>

<!-- Cruise configuration.  This number is for an A-4F (595mph/FL340) -->
<cruise speed="585" alt="34000">
  <control-setting axis="/controls/throttle[0]" value="0.8"/>
  <control-setting axis="/controls/flaps" value="0.0"/>
  <control-setting axis="/controls/gear-down" value="0"/>
</cruise>

<cockpit x="2.71" y="0.0" z="0.67"/>

<fuselage ax="5.61" ay="0" az="-0.66" bx="-6.59" by="0" bz=".64"
          width="2.0" taper="0.5" midpoint="0.3"/>

<wing x="-0.79" y=".55" z="-0.33" taper=".186"
      length="4.04" chord="3.95" sweep="28" dihedral="0" camber="0.02">
  <stall aoa="27" width="10" peak="1.3"/>
  <flap0 start="0.0" end="0.5" lift="1.3" drag="1.2"/>
  <flap1 start="0.5" end="1.0" lift="1.2" drag="1.2"/>
  <control-input axis="/controls/flaps" control="FLAP0"/>
  <control-input axis="/controls/aileron" control="FLAP1" split="true"/> 
  <control-input axis="/controls/aileron-trim" control="FLAP1" 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="-5.4" y="0" z="1.05" taper=".3" effectiveness="1.99"
       length="2.02" chord="2.02" sweep="26">
  <stall aoa="27" width="10" peak="1.5"/>
  <flap0 start="0" end="1" lift="1.6" drag="1.2"/>
  <control-input axis="/controls/elevator" control="FLAP0"/>
  <control-input axis="/controls/elevator-trim" control="FLAP0"/>
  <control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
</hstab>

<vstab x="-5.4" y="0" z="1.05" taper=".176"
       length="2.57" chord="3.11" sweep="28" effectiveness="1.5">
  <stall aoa="27" width="10" peak="1.5"/>
  <flap0 start="0" end="1" lift="1.15" drag="1.2"/>
  <control-input axis="/controls/rudder" control="FLAP0" invert="true"/>
  <control-input axis="/controls/rudder-trim" control="FLAP0" invert="true"/>
  <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"
		  min="1" max="-1"/>
</vstab>

<!-- P&W J52-P-6A turbojet, 8500 lbs sea level thrust -->
<jet x="0.61" y="0" z="0.11" mass="1800" thrust="8500" n1-max="106"
     exhaust-speed="2000">
  <control-input axis="/controls/throttle[0]" control="THROTTLE"/>
</jet>

<!-- nose -->
<gear x="3.32" y="0" z="-2.26" retract-time="7" compression=".96">
  <control-input axis="/controls/rudder" control="STEER" square="true"
                 src0="-1" src1="1" dst0="-0.9" dst1="0.9"/>
  <control-input axis="/controls/gear-down" control="EXTEND"/>
  <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
  <control-speed control="EXTEND" transition-time="7"/>
</gear>

<!-- left main -->
<gear x="-1.39" y="1.19" z="-1.89" retract-time="7" compression=".78"
      damp="2">
  <control-input axis="/controls/brakes[0]" control="BRAKE"/>
  <control-input axis="/controls/gear-down" control="EXTEND"/>
  <control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
  <control-speed control="EXTEND" transition-time="7"/>
  <control-speed control="BRAKE" transition-time="2"/>
</gear>

<!-- right main -->
<gear x="-1.39" y="-1.19" z="-1.89" retract-time="7" compression=".78"
      damp="2">
  <control-input axis="/controls/brakes[1]" control="BRAKE"/>
  <control-input axis="/controls/gear-down" control="EXTEND"/>
  <control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
  <control-speed control="EXTEND" transition-time="7"/>
  <control-speed control="BRAKE" transition-time="2"/>
</gear>

<!-- 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="0.17" jet="true" capacity="1678"/>
<tank x="-0.39" y="1" z="-0.33" jet="true" capacity="1750"/>
<tank x="-0.39" y="-1" z="-0.33" jet="true" capacity="1750"/>

<ballast x="4.11" y="0" z="0.67" mass="450"/> <!-- cockpit -->
<ballast x="2.61" y="0" z="0.67" mass="450"/> <!-- 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="-0.39" y="0" z="-1.33" size="1.5" 
        mass-prop="/yasim/a4/weights/center-lbs"/>
<weight x="-0.79" y="2" z="-1.33" size="1" 
        mass-prop="/yasim/a4/weights/left-inboard-lbs"/>
<weight x="-0.79" y="-2" z="-1.33" size="1" 
        mass-prop="/yasim/a4/weights/right-inboard-lbs"/>
<weight x="-1.39" y="3" z="-1.33" size="1" 
        mass-prop="/yasim/a4/weights/left-outboard-lbs"/>
<weight x="-1.39" y="-3" z="-1.33" size="1" 
        mass-prop="/yasim/a4/weights/right-outboard-lbs"/>

</airplane>