<airplane mass="10250"> <!-- Approach configuration --> <approach speed="120" aoa="16.5"> <control axis="/controls/throttle[0]" value="0.5"/> <control axis="/controls/flaps" value="1.0"/> </approach> <!-- Cruise configuration --> <cruise speed="517" alt="34000"> <control axis="/controls/throttle[0]" value="1.0"/> <control axis="/controls/flaps" value="0.0"/> </cruise> <cockpit x="-2.9" y="0.0" z="1.0"/> <fuselage ax="0" ay="0" az="0" bx="-12.2" by="0" bz=".64" width="1.47"/> <wing x="-6.4" y=".55" z="0" taper=".186" length="4.04" chord="3.95" sweep="28" dihedral="0" camber="0.1"> <stall aoa="25" width="10" peak="1.3"/> <flap0 start="0.0" end="0.5" lift="1.5" drag="2.0"/> <flap1 start="0.5" end="1.0" lift="1.15" drag="1.3"/> <control axis="/controls/flaps" output="FLAP0"/> <control axis="/controls/aileron" output="FLAP1" split="true"/> </wing> <hstab x="-11.01" y="0" z="1.38" taper=".3" effectiveness="2" length="2.02" chord="2.02" sweep="26"> <stall aoa="25" width="10" peak="1.5"/> <flap0 start="0" end="1" lift="1.7" drag="2.0"/> <control axis="/controls/elevator" output="FLAP0"/> <control axis="/controls/elevator-trim" output="FLAP0"/> </hstab> <vstab x="-11.01" y="0" z="1.38" taper=".176" length="2.57" chord="3.11" sweep="28"> <stall aoa="25" width="10" peak="1.5"/> <flap0 start="0" end="1" lift="1.15" drag="1.3"/> <control axis="/controls/rudder" output="FLAP0" invert="true"/> </vstab> <!-- NOTE: Skyhawks do NOT have afterburners. This one does for testing purposes only --> <jet x="-5.0" y="0" z=".44" mass="2050" thrust="10250" afterburner="16500"> <control axis="/controls/throttle[0]" output="THROTTLE"/> <control axis="/controls/afterburner[0]" output="REHEAT"/> </jet> <!-- nose --> <gear x="-2.29" y="0" z="-1.93" retract-time="7" compression=".96"> <control axis="/controls/rudder" output="STEER" square="true"/> </gear> <!-- left main --> <gear x="-7" y="1.19" z="-1.56" retract-time="7" compression=".78"> <control axis="/controls/brakes[0]" output="BRAKE"/> </gear> <!-- right main --> <gear x="-7" y="-1.19" z="-1.56" retract-time="7" compression=".78"> <control axis="/controls/brakes[1]" output="BRAKE"/> </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. --> <tank x="-5.50" y="0" z="0.5" jet="true" capacity="1880"/> <tank x="-6.0" y="1" z="0" jet="true" capacity="1750"/> <tank x="-6.0" y="-1" z="0" jet="true" capacity="1750"/> <ballast x="-1.5" y="0" z="1" mass="650"/> <!-- cockpit --> <ballast x="-3.0" y="0" z="1" mass="650"/> <!-- cockpit --> <ballast x="-11.01" y="0" z="1.38" mass="-300"/> <!-- lighten the tail --> </airplane>