120 lines
5.4 KiB
XML
120 lines
5.4 KiB
XML
<airplane mass="9853">
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<!-- Approach configuration -->
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<approach speed="130" aoa="13.5">
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<control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
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<control-setting axis="/controls/flight/flaps" value="1.0"/>
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<control-setting axis="/controls/gear/gear-down" value="1"/>
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</approach>
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<!-- Cruise configuration. This number is for an A-4F (595mph/FL340) -->
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<cruise speed="585" alt="34000">
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<control-setting axis="/controls/engines/engine[0]/throttle" value="0.8"/>
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<control-setting axis="/controls/flight/flaps" value="0.0"/>
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<control-setting axis="/controls/gear/gear-down" value="0"/>
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</cruise>
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<cockpit x="2.71" y="0.0" z="0.67"/>
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<fuselage ax="5.61" ay="0" az="-0.66" bx="-6.59" by="0" bz=".64"
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width="2.0" taper="0.5" midpoint="0.3"/>
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<wing x="-0.79" y=".55" z="-0.33" taper=".186"
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length="4.04" chord="3.95" sweep="28" dihedral="0" camber="0.02">
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<stall aoa="27" width="10" peak="1.3"/>
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<flap0 start="0.0" end="0.5" lift="1.3" drag="1.2"/>
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<flap1 start="0.5" end="1.0" lift="1.2" drag="1.2"/>
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<control-input axis="/controls/flight/flaps" control="FLAP0"/>
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<control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
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<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
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<control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
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<control-output control="FLAP1" side="left"
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prop="/surface-positions/left-aileron-pos-norm"/>
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<control-output control="FLAP1" side="right"
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prop="/surface-positions/right-aileron-pos-norm"/>
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<control-speed control="FLAP0" transition-time="5"/>
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</wing>
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<hstab x="-5.4" y="0" z="1.05" taper=".3" effectiveness="1.99"
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length="2.02" chord="2.02" sweep="26">
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<stall aoa="27" width="10" peak="1.5"/>
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<flap0 start="0" end="1" lift="1.6" drag="1.2"/>
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<control-input axis="/controls/flight/elevator" control="FLAP0"/>
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<control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
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<control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
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</hstab>
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<vstab x="-5.4" y="0" z="1.05" taper=".176"
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length="2.57" chord="3.11" sweep="28" effectiveness="1.5">
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<stall aoa="27" width="10" peak="1.5"/>
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<flap0 start="0" end="1" lift="1.15" drag="1.2"/>
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<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
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<control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
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<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"
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min="1" max="-1"/>
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</vstab>
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<!-- P&W J52-P-6A turbojet, 8500 lbs sea level thrust -->
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<jet x="0.61" y="0" z="0.11" mass="1800" thrust="8500" n1-max="106"
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exhaust-speed="2000">
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<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
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</jet>
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<!-- nose -->
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<gear x="3.32" y="0" z="-2.26" retract-time="7" compression=".96">
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<control-input axis="/controls/flight/rudder" control="STEER" square="true"
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src0="-1" src1="1" dst0="-0.9" dst1="0.9"/>
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<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
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<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
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<control-speed control="EXTEND" transition-time="7"/>
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</gear>
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<!-- left main -->
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<gear x="-1.39" y="1.19" z="-1.89" retract-time="7" compression=".78"
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damp="2">
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<control-input axis="/controls/gear/wheel[0]/brake" control="BRAKE"/>
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<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
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<control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
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<control-speed control="EXTEND" transition-time="7"/>
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<control-speed control="BRAKE" transition-time="2"/>
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</gear>
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<!-- right main -->
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<gear x="-1.39" y="-1.19" z="-1.89" retract-time="7" compression=".78"
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damp="2">
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<control-input axis="/controls/gear/wheel[1]/brake" control="BRAKE"/>
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<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
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<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
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<control-speed control="EXTEND" transition-time="7"/>
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<control-speed control="BRAKE" transition-time="2"/>
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</gear>
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<!-- A4-M had 800 gallons of in-fuselage fuel capacity in three tanks,
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one in each wing and one behind the cockpit. TA-4F had "only" 100
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gallons in the fuselage due to the second seat, so the wings must
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have 0-350 gallons each. Call the tanks 260/280/260 gallons, and
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use 6.72 lbs/gal for Jet-A fuel. BUT: this is an A-4E, which had
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770 gallons. Figure that the extra 30 all went into an expanded
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center tank underneath the new "hump" in the fuselage. -->
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<tank x="0.11" y="0" z="0.17" jet="true" capacity="1678"/>
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<tank x="-0.39" y="1" z="-0.33" jet="true" capacity="1750"/>
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<tank x="-0.39" y="-1" z="-0.33" jet="true" capacity="1750"/>
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<ballast x="4.11" y="0" z="0.67" mass="450"/> <!-- cockpit -->
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<ballast x="2.61" y="0" z="0.67" mass="450"/> <!-- cockpit -->
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<!-- The early A-4's had five pylons. One 3500lbs center for a tank,
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two inboard pylons holding 2250lbs, and two 1000lbs outboard
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pylons. -->
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<weight x="-0.39" y="0" z="-1.33" size="1.5"
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mass-prop="/yasim/a4/weights/center-lbs"/>
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<weight x="-0.79" y="2" z="-1.33" size="1"
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mass-prop="/yasim/a4/weights/left-inboard-lbs"/>
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<weight x="-0.79" y="-2" z="-1.33" size="1"
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mass-prop="/yasim/a4/weights/right-inboard-lbs"/>
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<weight x="-1.39" y="3" z="-1.33" size="1"
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mass-prop="/yasim/a4/weights/left-outboard-lbs"/>
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<weight x="-1.39" y="-3" z="-1.33" size="1"
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mass-prop="/yasim/a4/weights/right-outboard-lbs"/>
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</airplane>
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