<airplane mass="9853"> <!-- Approach configuration --> <approach speed="130" aoa="13.5"> <control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/> <control-setting axis="/controls/flight/flaps" value="1.0"/> <control-setting axis="/controls/gear/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/engines/engine[0]/throttle" value="0.8"/> <control-setting axis="/controls/flight/flaps" value="0.0"/> <control-setting axis="/controls/gear/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/flight/flaps" control="FLAP0"/> <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="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/flight/elevator" control="FLAP0"/> <control-input axis="/controls/flight/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/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"/> </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/engines/engine[0]/throttle" control="THROTTLE"/> </jet> <!-- nose --> <gear x="3.32" y="0" z="-2.26" retract-time="7" compression=".96"> <control-input axis="/controls/flight/rudder" control="STEER" square="true" src0="-1" src1="1" dst0="-0.9" dst1="0.9"/> <control-input axis="/controls/gear/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/gear/wheel[0]/brake" control="BRAKE"/> <control-input axis="/controls/gear/parking-brake" 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"/> <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/gear/wheel[1]/brake" control="BRAKE"/> <control-input axis="/controls/gear/parking-brake" 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"/> <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>