99 lines
No EOL
4.2 KiB
XML
99 lines
No EOL
4.2 KiB
XML
<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="-2.9" y="0.0" z="1.0"/>
|
|
|
|
<fuselage ax="0" ay="0" az="0" bx="-12.2" by="0" bz=".64"
|
|
width="2.0" taper="0.5" midpoint="0.3"/>
|
|
|
|
<wing x="-6.4" y=".55" z="0" 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="1.4" drag="1.2"/>
|
|
<flap1 start="0.5" end="1.0" lift="1.25" drag="1.3"/>
|
|
<control-input axis="/controls/flaps" control="FLAP0"/>
|
|
<control-input axis="/controls/aileron" 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="-11.01" y="0" z="1.38" 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="1.7" 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="-11.01" y="0" z="1.38" 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-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="-5.0" y="0" z=".44" mass="1800" thrust="8500">
|
|
<control-input axis="/controls/throttle[0]" control="THROTTLE"/>
|
|
</jet>
|
|
|
|
<!-- nose -->
|
|
<gear x="-2.29" y="0" z="-1.93" 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="-7" y="1.19" z="-1.56" retract-time="7" compression=".78">
|
|
<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"/>
|
|
</gear>
|
|
|
|
<!-- right main -->
|
|
<gear x="-7" y="-1.19" z="-1.56" retract-time="7" compression=".78">
|
|
<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"/>
|
|
</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 the expanded
|
|
center tank. -->
|
|
<tank x="-5.50" y="0" z="0.5" jet="true" capacity="1678"/>
|
|
<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="450"/> <!-- cockpit -->
|
|
<ballast x="-3.0" y="0" z="1" mass="450"/> <!-- cockpit -->
|
|
|
|
</airplane> |