CVS: data/Aircraft/UH-1 hhs-uh1.xml,NONE,1.1
Emmanuel Baranger <[email protected]>
| Newsgroups | gmane.games.flightgear.cvc |
|---|---|
| Message-ID | <[email protected]> |
Update of /var/cvs/FlightGear-0.9/data/Aircraft/UH-1
In directory baron.flightgear.org:/tmp/cvs-serv15198
Added Files:
hhs-uh1.xml
Log Message:
- bad FDM by HHS (But you can test)
--- NEW FILE "hhs-uh1.xml" ---
<?xml version="1.0" encoding="UTF-8"?>
<!--
FDM based on information given in NASA-CR-3144; TR-1087-1
and NASA-CR-3145
UH-1GunshipH DESCRIPTIVE DATA
MAIN ROTOR
Blades 2
Radius 7.32 m (24 f t )
Chord 0.333 m (1.75 f t )
Section NACA 0012
Hub type Teetering
Undersling 0.132 m (0.433 f t )
Twist -10.9 deg
Pitch flap coupling (Fj3) Zero
Shaft tilt 5 deg forward
Design rpm
Hub loca&on
Blade flapping inertia 1641.2 kg-m (1210.5 slug-ft )
314 to 324 (power on), 294 t o 339 (power off)
FS 133.3, WL 136.5
2 2
TAIL ROTOR
Blades 2
Diameter 2.59 m (8.3 f t )
Chord 0.297 m (0.958 f t )
Twist Zero
Gear ratio 5.123
Hub location FS 479.4, WL 137.6, BL -15.16
ELEXATOR (EACH SIDE, EXCLUDING FUSELAGE CARRY-THROUGH)
Area 1.016 m2 (10.936 ft2)
Aspect ratio 2.009
Center of pressure location
Incidence Variable
FS 363.0, BL - i- 28.1, WL 64.83
VERTICAL STABILIZER
Area
Aspect ratio 1 .&6
Center of pressure location
1.036 m2 (11 .I5 ft2)
FS 450.3, BL 0.4, WL 104.7
-->
<airplane mass="5200">
<approach speed="80" aoa="16">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
</approach>
<cruise speed="84" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
</cruise>
<!-- x="4.954" y="0.0" z="1.821" -->
<rotor name="main"
x="4.92" y="0.0" z="1.233"
nx="0.0875" ny="0" nz="1."
fx="1" fy="0" fz="0" ccw="1"
maxcollective="15.5" mincollective=".5"
mincyclicele="-24" maxcyclicele="24"
mincyclicail="-16" maxcyclicail="24"
diameter="14.63" numblades="2"
weightperblade="120" twist="-10.9"
chord="0.533" rpm="324"
relbladecenter="0.5" dynamic=".3"
rellenflaphinge="0.018"
sharedflaphinge="1"
delta3="0" delta=".25"
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"
taper="1"
number-of-segments="8" number-of-parts="8"
rel-len-where-incidence-is-measured="0.7" rel-len-blade-start="0.16"
airfoil-lift-coefficient="4.4" airfoil-drag-coefficient0="0.00525" airfoil-drag-coefficient1="0.07"
incidence-stall-zero-speed="24" incidence-stall-half-sonic-speed="19.5"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="8.0"
cyclic-factor="0.95"
rotor-correction-factor="0.93"
downwashfactor ="0.3"
balance="0.990">
<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="true"/>
<control-input axis="/controls/flight/aileron" control="CYCLICAIL" src0="-1.0" src1="1.0" dst0="-0.35" dst1="0.35"/>
<control-input axis="/controls/flight/elevator-trim" control="CYCLICELE" split="true"/>
<control-input axis="/controls/flight/elevator" control="CYCLICELE" src0="-1.0" src1="1.0" dst0="-0.35" dst1="0.35"/>
<control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE" src0="0.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/rotors/bar/roll-deg" control="CYCLICAIL" src0="-20" src1="20" dst0=".16" dst1="-.16"/>
<control-input axis="/rotors/bar/yaw-deg" control="CYCLICELE" src0="-24" src1="24" dst0="-.16" dst1=".16"/>
</rotor>
<!-- x="-4.026" y="-0.071" z="1.386" -->
<rotor name="tail"
x="-3.87" y="-0.473" z="1.12"
nx="0.00" ny="-1" nz="-0.00"
fx="1" fy="0" fz="0" ccw="1" phi0="70"
maxcollective="20" mincollective="-9.3"
diameter="2.6" numblades="2"
chord="0.297" twist="0"
weightperblade="30" relbladecenter="0.7"
dynamic="1" rpm="1620" rellenflaphinge="0.0" delta3="1" translift="0" delta="0.5" pitch-a="10" pitch-b="15"
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"
notorque="0" taper="1" number-of-segments="5" number-of-parts="4" rel-len-blade-start="0.33"
downwashfactor ="0.3"
rotor-correction-factor="0.995">
<control-input axis="/controls/flight/rudder" control="COLLECTIVE" invert="true" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
</rotor>
<rotor name="bar"
x="4" y="0.0" z="2.5"
nx="0.05" ny="0" nz="1."
fx="1" fy="0" fz="0" ccw="1"
diameter="3" numblades="2"
mintiltpitch=" -10"
maxtiltpitch="10"
mintiltroll="-10"
maxtiltroll=" 10"
weightperblade="50"
chord="0.001" rpm="324"
relbladecenter="0.95" dynamic=".25"
rellenflaphinge="0.000000"
flapmin="-25" flapmax="25"
delta3="0" delta=".25"
flap0="-0.5" flap0factor="0"
notorque="0" dragfactor="0.30"
taper="1"
number-of-segments="3" number-of-parts="4"
rel-len-where-incidence-is-measured="0.7" rel-len-blade-start="0.16"
airfoil-lift-coefficient="0.0000001" airfoil-drag-coefficient0="0.000075" airfoil-drag-coefficient1="0.0"
incidence-stall-zero-speed="29" incidence-stall-half-sonic-speed="29"
lift-factor-stall="0"
stall-change-over="5.5"
drag-factor-stall="1.0"
cyclic-factor="0.8"
rotor-correction-factor="0.98" >
</rotor>
<rotorgear max-power-engine="1044"
max-power-rotor-brake="185"
rotorgear-friction="3.7"
engine-prop-factor="0.015"
engine-accel-limit="4"
yasimdragfactor="40"
yasimliftfactor="240">
<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
<control-input axis="/controls/rotor/brake" control="ROTORBRAKE" src0="0.0" src1="1.0" dst0="0.0" dst1="1.0"/>
<control-input axis="/controls/rotor/reltarget" control="ROTORRELTARGET" src0="0.0" src1="2.0" dst0="0.0" dst1="2.0"/>
<control-input axis="/controls/rotor/maxreltorque" control="ROTORENGINEMAXRELTORQUE" src0="0.0" src1="2.0" dst0="0.0" dst1="2.0"/>
</rotorgear>
<cockpit x="7.589" y="0.694" z="-0.570"/>
<!-- Fuse -->
<!-- ax="8.897" ay="0" az="-0.622" bx="2.212" by="0" bz="-0.622" -->
<fuselage ax="8" ay="0" az="-0.6" bx="-2.6" by="0" bz="-0.6" cx="1.5" cy="1.0" cz="0.50" width="2.6" taper="0.7" midpoint="0.45" idrag="0"/>
<!-- Tail -->
<!-- ax="2.212" ay="0" az="-0.623" bx="-3.537" by="0" bz="-0.033" -->
<fuselage ax="-2.6" ay="0" az="-0.6" bx="-3.4" by="0" bz="-0.0" cx="1.0" cy="1.0" cz=".2" width="0.6" taper="0.5" midpoint="0" idrag="0"/>
<vstab x="-2.9" y="0" z="0.0"
taper=".5"
length="2.0"
chord="0.9"
sweep="45"
incidence="-0">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<hstab x="-1.1" y="0.0" z="-0.3"
taper="1.0"
incidence="15"
effectiveness="0.25"
length="1.0131"
chord="0.5"
sweep="0"
>
<stall aoa="16" width="4" peak="1.5"/>
<flap0 start="0" end="1" lift="1.6" drag="1.2"/>
<control-input axis="/controls/flight/elevator" control="FLAP0"/>
<control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
<control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
</hstab>
<!-- left skid -->
<gear x="6.444" y="1.256" z="-1.994"
skid="1"
compression="0.10"
spring="8"
sfric="0.5"
dfric="0.4"/>
<gear x="3.558" y="1.256" z="-1.859"
skid="1"
compression="0.10"
spring="8"
sfric="0.5"
dfric="0.4"/>
<!-- right skid -->
<gear x="6.444" y="-1.256" z="-1.994"
skid="1"
compression="0.10"
spring="8"
sfric="0.5"
dfric="0.4"/>
<gear x="3.558" y="-1.256" z="-1.859"
skid="1"
compression="0.10"
spring="8"
sfric="0.5"
dfric="0.4"/>
<!-- tail skid -->
<gear x="-4.3" y="0.00" z="-0.55"
skid="1"
compression="0.01"
spring="0.1"
sfric="1"
dfric="1"/>
<tank x="4.5" y="-0.5" z="-1.4" capacity="1400"/>
<!-- work around bug in native-fdm.cxx:184 -->
<tank x="0" y="0" z="0" capacity="0"/>
<ballast x="+9.2" y="+0.0" z=" -4.9" mass="500"/>
<ballast x="+8.3" y="-0.0" z=" 0" mass="-500"/>
<ballast x="+1.7" y=" 0.0" z=" 0" mass="-500"/>
<ballast x="+5" y="-1.3" z=" 0" mass="500"/>
<ballast x="+5" y=" 1.3" z=" 0" mass="500"/>
<ballast x="+5" y="+0.0" z=" -2.1" mass="-500"/>
<ballast x="+5" y="+0.0" z=" 2.1" mass="-500"/>
<ballast x="+5" y="+0.0" z=" -0.0" mass="4000"/>
<weight x="7.4" y=".65" z="-.7" mass-prop="/sim/weight[0]/weight-lb"/>
<!-- pilot -->
<weight x="7.4" y="-.65" z="-.7" mass-prop="/sim/weight[1]/weight-lb"/>
<!-- co-pilot -->
<weight x="5.3" y=".8" z="-.7" mass-prop="/sim/weight[2]/weight-lb"/>
<!-- right passenger -->
<weight x="5.3" y="-.8" z="-.7" mass-prop="/sim/weight[4]/weight-lb"/>
<!-- left passenger -->
<weight x="4.9" y="0" z="-1.3" mass-prop="/sim/weight[5]/weight-lb"/>
<!-- load -->
</airplane>
------------------------------------------------------------------------------
Download Intel® Parallel Studio Eval
Try the new software tools for yourself. Speed compiling, find bugs
proactively, and fine-tune applications for parallel performance.
See why Intel Parallel Studio got high marks during beta.
http://p.sf.net/sfu/intel-sw-dev