/
H-21C-yasim.xml
executable file
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H-21C-yasim.xml
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<?xml version="1.0"?>
<!--General characteristics
Crew: 2
Capacity:
22 troops or
12 stretchers
Length: 52 ft 6 in (16.0 m)
Rotor diameter: 44 ft 0 in (13.4 m)
Height: 15 ft 9 in (4.80 m)
Disc area: 3,041 ft² (282.7 m²)
Empty weight: 8,950 lb (4,058 kg)
Loaded weight: 15,200 lb (6,893 kg)
Powerplant: 1× Wright R-1820-103 radial engine, 1,425 hp (1,063 kW) driving 2 rotors
Performance
Cruise speed: 98 mph (85 kn, 158 km/h)
Maximum speed: 127 mph (110 kn, 204 km/h)
Range: 265 mi (230 nmi, 426 km)
Service ceiling: 9,450 ft (2,880 m)
Disc loading: 5 lb/ft² (24 kg/m²)
Power/mass: 0.09 hp/lb (150 W/kg)
NACA 0012
Rotorachsabstand
12,87 m
H-21 Work Horse, Boeing-Vertol
(M-USA-H-C-2R4-N-AR1)
Development of {HRP} tandem rotor helicopter for the USAF. The
H-21 had a high upswept tail, to lift the aft rotor above the
front rotor. Over 500 were built.
Type: H-21C
Function: transport
Year: 1952 Crew: 2 Engines: 1 * 1050kW Wright R-1820-103
Rotor Span: 13.41m Length: 26.31m Height: 4.70m Disc Area:282.52m2
Empty Weight: 3629kg Max.Weight: 6668kg
Speed: 211km/h Ceiling: 2360m Range: 640km
Load: 20 seats, 2130kg
-->
<!--Missing most of the right data, however learned and made from FDM ch47.xml and s51.xml both by Maik Justus -->
<airplane mass="8950">
<!-- Configurations-->
<!-- Approach configuration -->
<approach speed="60" aoa="12">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
<control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="1.0"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="110" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
<control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
</cruise>
<!-- Rotors -->
<!-- Rotor MAIN -->
<rotor name="main" x="6.62" y="0.0" z="2.08" nx="-0.00" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="0"
maxcollective="100" mincollective="-100"
mincyclicele="-100" maxcyclicele="100"
mincyclicail="-15" maxcyclicail="15"
diameter="12.9" numblades="3" weightperblade="140" relbladecenter="0.5"
dynamic="1" rpm="262" rellenflaphinge="0.140" delta3="0"
delta=".18"
pitch-a="10"
pitch-b="15"
flapmin="-15"
flapmax="15"
flap0="-5"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="20"
translift-maxfactor="1.3"
ground-effect-constant="0.1"
twist="-8.5"
taper="1"
chord="0.54"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.11"
rotor-correction-factor="0.8"
airfoil-lift-coefficient="6.3"
airfoil-drag-coefficient0="0.0075"
airfoil-drag-coefficient1="0.1"
incidence-stall-zero-speed="18"
incidence-stall-half-sonic-speed="9"
lift-factor-stall="0.18" stall-change-over="5.5"
drag-factor-stall="8.0"
cyclic-factor="0.8">
<control-input axis="/controls/flight/rudder" control="CYCLICAIL"
src0="-1.0" src1="1.0"
dst0="-0.2" dst1="0.2"/>
<control-input axis="/controls/flight/aileron" control="CYCLICAIL"
src0="-1.0" src1="1.0"
dst0="-0.3" dst1="0.3"/>
<!-- I do not found the right way to manage the trim action on top speed.
So I map the control to the elevator-trim property and make a setlistener to the input
property elevator.
<control-input axis="/controls/flight/elevator" control="COLLECTIVE"
src0="-1.0" src1="1.0"
dst0="0.02" dst1="-0.04"/>
-->
<control-input axis="/controls/flight/elevator-h21" control="COLLECTIVE"
src0="-1.0" src1="1.0"
dst0="0.02" dst1="-0.04"/>
<control-input axis="/controls/engines/engine[1]/throttle" control="COLLECTIVE"
src0="0.0" src1="1.0"
dst0="0.14" dst1="0.02"/>
</rotor>
<!-- Rotor TAIL -->
<rotor name="tail" x="-6.25" y="0.0" z="2.4" nx="-0.00" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
maxcollective="100" mincollective="-100"
mincyclicele="-100" maxcyclicele="100"
mincyclicail="-15" maxcyclicail="15"
diameter="12.9" numblades="3" weightperblade="140" relbladecenter="0.5"
dynamic="1" rpm="262" rellenflaphinge="0.140" delta3="0"
delta=".18"
pitch-a="10"
pitch-b="15"
flapmin="-15"
flapmax="15"
flap0="-5"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="20"
translift-maxfactor="1.3"
ground-effect-constant="0.1"
twist="-8.5"
taper="1"
chord="0.54"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.11"
rotor-correction-factor="0.8"
airfoil-lift-coefficient="6.3"
airfoil-drag-coefficient0="0.0075"
airfoil-drag-coefficient1="0.1"
incidence-stall-zero-speed="18"
incidence-stall-half-sonic-speed="9"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="8.0"
cyclic-factor="0.8">
<control-input axis="/controls/flight/rudder" control="CYCLICAIL" invert="true"
src0="-1.0" src1="1.0"
dst0="-0.2" dst1="0.2"/>
<control-input axis="/controls/flight/aileron" control="CYCLICAIL"
src0="-1.0" src1="1.0"
dst0="-0.3" dst1="0.3"/>
<!-- I do not found the right way to manage the trim action on top speed.
So I map the control to the elevator-trim property and make a setlistener to the input
property elevator.
<control-input axis="/controls/flight/elevator" control="COLLECTIVE"
src0="-1.0" src1="1.0"
dst0="0.02" dst1="-0.04"/>
-->
<control-input axis="/controls/flight/elevator-h21" control="COLLECTIVE"
src0="-1.0" src1="1.0"
dst0="-0.04" dst1="0.02"/>
<control-input axis="/controls/engines/engine[1]/throttle" control="COLLECTIVE"
src0="0.0" src1="1.0"
dst0="0.14" dst1="0.02"/>
</rotor>
<!-- Rotorgear -->
<rotorgear
max-power-engine="1425"
max-power-rotor-brake="100"
rotorgear-friction="1.4"
engine-prop-factor="0.005"
engine-accel-limit="10"
yasimdragfactor="16"
yasimliftfactor="180"
>
<control-input axis="/controls/engines/engine[0]/rotorgear" control="ROTORGEARENGINEON"/>
<control-input axis="/controls/rotor/brake" control="ROTORBRAKE"
src0="0.0" src1="1.0"
dst0="0.0" dst1="1.0"/>
</rotorgear>
<!-- Cockpit -->
<cockpit x="6.8" y=".33" z="0.6"/>
<!-- Fuselage -->
<fuselage ax="8.4" ay="0" az="0.0" bx="6.8" by="0" bz="0.2" cx="0.35" cy="1.2" cz="0.5" width="2.2" taper="0.5" midpoint="1.0"/>
<fuselage ax="6.8" ay="0" az="0.2" bx="-0.4" by="0" bz="-0.6" cx="0.35" cy="1.2" cz="0.5" width="2.2" taper="1" midpoint="0.5"/>
<fuselage ax="-0.4" ay="0" az="-0.6" bx="-6.0" by="0" bz="0.6" cx="0.35" cy="1.2" cz="0.5" width="2.2" taper="1" midpoint="0.5"/>
<fuselage ax="-6.0" ay="0" az="0.6" bx="-7.5" by="0" bz="0.8" cx="0.75" cy="1.2" cz="1.5" width="2.2" taper="0.3" midpoint="0.0"/>
<vstab x="-6.35" y="2.1" z="-0.50" taper="1.0" length="2.3" chord="1.40" sweep="0" incidence="0">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-6.35" y="-2.1" z="-0.50" taper="1.0" length="2.3" chord="1.40" sweep="0" incidence="0">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<hstab x="-6.40" y="0" z="0.62" taper="0.7" length="2.1" chord="1.60" sweep="-2" incidence="2">
<stall aoa="16" width="4" peak="1.5"/>
</hstab>
<!-- Gear -->
<!--nose-->
<gear x="6.15593" y="+0.00" z="-2.67592" compression="0.30" spring="1.35" damp="0.31" sfric="0.5" dfric="0.7">
<control-input axis="/controls/flight/rudder" control="STEER" square="true" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
</gear>
<!-- left -->
<gear x="-1.24112" y="+2.09215" z="-2.79549" compression="0.53" spring="0.98" damp="0.25" sfric="0.5" dfric="0.7">
<control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<!-- right -->
<gear x="-1.24112" y="-2.09215" z="-2.79549" compression="0.53" spring="0.98" damp="0.25" sfric="0.5" dfric="0.7">
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<!-- Tanks-->
<tank x="-1.50" y="0" z="0" capacity="900"/>
<tank x="-1.50" y="0" z="0" capacity="900"/>
<!-- Ballast-->
<!-- Ballast fuselage front-->
<ballast x="2.5" y="-1" z="-1.0" mass="2000"/>
<ballast x="2.5" y="1" z="-1.0" mass="2000"/>
<ballast x="6.0" y="0" z="-1.0" mass="800"/>
<!-- Ballast fuselage rear-->
<ballast x="-4.5" y="-1" z="-1" mass="1500"/>
<ballast x="-4.5" y="1" z="-1" mass="1500"/>
<ballast x="-3.5" y="0" z="1" mass="800"/>
<!-- Load ballast-->
<!-- pilots -->
<weight x="6.8" y="0" z="0" mass-prop="/sim/weight[0]/weight-lb"/>
<!-- passengers front - Left side-->
<weight x="4" y="-0.8" z="-0.7" mass-prop="/sim/weight[1]/weight-lb"/>
<!-- passengers front - Right side-->
<weight x="4" y="0.8" z="-0.7" mass-prop="/sim/weight[2]/weight-lb"/>
<!-- passengers rear - Left side-->
<weight x="1" y="-0.8" z="-1.4" mass-prop="/sim/weight[3]/weight-lb"/>
<!-- passengers rear - Right side-->
<weight x="1" y="0.8" z="-1.4" mass-prop="/sim/weight[4]/weight-lb"/>
<!-- balast for SAR procedure -->
<weight x="2" y="0.0" z="-5.0" mass-prop="/sim/weight[5]/weight-lb"/>
</airplane>