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