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Aircraft-yasim/yf23-yasim.xml
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Aircraft-yasim/yf23-yasim.xml
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<!-- There weren't many YF23s - just the two prototypes - and I
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couldn't find much 'hard' information so a lot of this fdm is
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guess work (GW).
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-->
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<!-- Max take off weight is 64000lb so I'm allocating 4xAIM-9,
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4x AIM-120, pilot and fuel and adding them as ballast entries
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until I sort out correct weight entries.
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GW figures for these are
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Aim-9 200lb x 4 = 8000lb
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AIM-120 400lb x 4 = 16000lb
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Pilot 200lb x 1 = 200lb
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Fuel 24000lb x 1 = 24000lb (from a web-site)
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-->
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<airplane mass="40000">
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<!-- Approach configuration -->
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<!-- From GW & photos -->
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<approach speed="110" aoa="7">
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<control-setting axis="/controls/throttle[0]" value="0.05"/>
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<control-setting axis="/controls/throttle[1]" value="0.05"/>
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<control-setting axis="/controls/flaps" value="0.7"/>
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<!--
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<control-setting axis="/controls/slats" value="0.3"/>
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-->
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<control-setting axis="/controls/gear-down" value="1"/>
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</approach>
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<!-- Cruise configuration -->
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<cruise speed="900" alt="35000">
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<control-setting axis="/controls/throttle[0]" value="1.0"/>
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<control-setting axis="/controls/flaps" value="0.0"/>
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<!--
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<control-setting axis="/controls/slats" value="0.0"/>
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-->
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<control-setting axis="/controls/gear-down" value="0"/>
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</cruise>
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<cockpit x="5.70" y="0.00" z="1.26"/>
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<!-- Fuselage entries for the fuselage proper and the two
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engine housings. The YF23 is basically a wing with
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these three fuselage/housings, and the elevator. For
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this reason I've started the wings from the center-line.
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-->
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<!-- Fuselage proper -->
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<fuselage ax="10.00" ay="0.00" az="0.00"
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bx="-2.00" by="0.00" bz="0.00"
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width="1.6" taper="0.1" midpoint="0.3"/>
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<!-- Left engine housing (Excl intakes) -->
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<fuselage ax="-2.00" ay="1.80" az="0.00"
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bx="-8.00" by="1.20" bz="0.60"
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width="1.2" taper="0.1" midpoint="0.3"/>
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<!-- Right engine housing (Excl intakes) -->
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<fuselage ax="-2.00" ay="-1.80" az="0.00"
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bx="-8.00" by="-1.20" bz="0.60"
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width="1.2" taper="0.1" midpoint="0.3"/>
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<!-- GW stall characteristics -->
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<wing x="-2.00" y="0.00" z="0.25" length="6.66" chord="12.00"
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taper="0.08" sweep="0" dihedral="0" camber="0.0">
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<stall aoa="58" width="1" peak="1.3"/>
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<flap0 start="0.36" end="0.63" lift="1.2" drag="1.4"/>
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<flap1 start="0.63" end="0.89" lift="1.1" drag="1.1"/>
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<!--
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<slat start="0.42" end="0.89" aoa="3" drag="1.1"/>
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-->
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<control-input axis="/controls/flaps" control="FLAP0"/>
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<control-input axis="/controls/aileron" control="FLAP1" split="true"/>
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<!--
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<control-input axis="/controls/slats" control="SLAT"/>
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-->
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<control-input axis="/controls/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" prop="/surface-positions/left-aileron-pos-norm"/>
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<control-output control="FLAP1" side="right" prop="/surface-positions/right-aileron-pos-norm"/>
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<!--
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<control-output control="SLAT" side="left" prop="/surface-positions/left-slat-pos-norm"/>
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<control-output control="SLAT" side="right" prop="/surface-positions/right-slat-pos-norm"/>
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-->
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<control-speed control="FLAP0" transition-time="10"/>
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<control-speed control="FLAP1" transition-time="0.5"/>
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</wing>
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<hstab x="-8.60" y="2.40" z="0.36" length="3.30" chord="5.10"
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taper="0.11" sweep="0" dihedral="40" effectiveness="-2.5">
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<stall aoa="
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22
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" width="2" peak="1.3"/>
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<flap0 start="0" end="1" lift="1.1" drag="1.2"/>
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<control-input axis="/controls/elevator" control="FLAP0"/>
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<control-input axis="/controls/elevator-trim" control="FLAP0"/>
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<control-output control="FLAP0" side="left" prop="/surface-positions/left-elevator-pos-norm"/>
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<control-output control="FLAP0" side="right" prop="/surface-positions/right-elevator-pos-norm"/>
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<control-speed control="FLAP0" transition-time="0.5"/>
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</hstab>
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<!-- The only figures I've found for the F119-PW-100L give 35000lb
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'class' with afterburner. The difference between the top speed
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with and with out afterburner (mach 1.43 vs mach 2) suggests that
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the afterburner ratio is << 2:1 so I've used a ratio suggested by
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those mach speeds + plus a fudge factor = 0.7. Also, the engine has
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thrust vectoring but I've not worked that out yet.
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-->
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<jet x="-6.26" y="1.20" z="0.60" mass="3000" thrust="24500" afterburner="35000">
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<control-input axis="/controls/throttle[0]" control="THROTTLE"/>
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<control-input axis="/controls/afterburner[0]" control="REHEAT"/>
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</jet>
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<jet x="-6.26" y="-1.20" z="0.60" mass="3000" thrust="24500" afterburner="35000">
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<control-input axis="/controls/throttle[1]" control="THROTTLE"/>
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<control-input axis="/controls/afterburner[1]" control="REHEAT"/>
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</jet>
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<!-- Front -->
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<gear x="5.25" y="0.00" z="-2.25" compression="0.65" spring="2.0">
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<control-input axis="/controls/rudder" control="STEER" square="true"/>
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<!--
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<control-input axis="/controls/brakes[0]" control="BRAKE"/>
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-->
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<control-input axis="/controls/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="4"/>
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<control-output control="STEER" prop="/gear/gear[0]/steering-norm"/>
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</gear>
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<!-- Left main -->
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<!--
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<gear x="-2.20" y="1.92" z="-2.7" compression="1.2" spring="1.5">
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-->
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<gear x="-2.20" y="1.92" z="-2.25" compression="0.65" spring="1.5">
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<control-input axis="/controls/brakes[0]" control="BRAKE"/>
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<control-input axis="/controls/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="4"/>
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</gear>
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<!-- Right main -->
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<!--
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<gear x="-2.20" y="1.92" z="-2.7" compression="1.2" spring="1.5">
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-->
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<gear x="-2.20" y="-1.92" z="-2.25" compression="0.65" spring="1.5">
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<control-input axis="/controls/brakes[0]" control="BRAKE"/>
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<control-input axis="/controls/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="4"/>
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</gear>
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<!-- Canopy -->
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<gear x="4.1" y="0.0" z="1.05" retract-time="7" compression="0.6">
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<control-input axis="/controls/parking-brake" control="EXTEND"/>
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<control-speed control="EXTEND" transition-time="10"/>
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<control-output control="EXTEND" prop="/canopy/position-norm"/>
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</gear>
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<!-- The locations and capcities are GW. -->
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<!-- Fuselage tank -->
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<tank x="1.5" y="0" z="0.68" jet="true" capacity="8000"/>
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<!-- Left wing tank -->
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<tank x="-1.40" y="2" z="0.0" jet="true" capacity="8000"/>
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<!-- Right wing tank -->
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<tank x="-1.40" y="-2" z="0.0" jet="true" capacity="8000"/>
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<!-- Avionics -->
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<ballast x="4" y="0" z="0.6" mass="3000"/>
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<!-- Cockpit and radar -->
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<ballast x="7" y="0" z="0.2" mass="1500"/>
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<!-- Pilot -->
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<ballast x="5.8" y="0" z="0.6" mass="200"/>
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<!-- AIM-9 x 2 Left -->
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<ballast x="-0.85" y="2.40" z="-0.23" mass="200"/>
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<ballast x="-0.85" y="2.24" z="-0.46" mass="200"/>
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<!-- AIM-9 x 2 Right -->
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<ballast x="-0.85" y="-2.40" z="-0.23" mass="200"/>
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<ballast x="-0.85" y="-2.24" z="-0.46" mass="200"/>
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<!-- AIM-120 x 2 Left -->
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<ballast x="-1.2" y="2.02" z="-0.52" mass="400"/>
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<ballast x="-1.2" y="1.74" z="-0.52" mass="400"/>
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<!-- AIM-120 x 2 Left -->
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<ballast x="-1.2" y="-2.02" z="-0.52" mass="400"/>
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<ballast x="-1.2" y="-1.74" z="-0.52" mass="400"/>
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<!-- Trim ballast -->
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<ballast x="6" y="0" z="0.0" mass="1000"/>
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</airplane>
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