/
ec145.xml
216 lines (173 loc) · 7.21 KB
/
ec145.xml
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<!-- official RD + x.xx m = yasim RD (reference datum) -->
<!-- FDM based also on information given in NASA-CR-3144; TR-1087-1 for the bo105 and adapted to fit- and further adapted for the EC145 by StuartC-->
<!--
<airplane mass="3951">
-->
<airplane mass="3951" version="YASIM_VERSION_CURRENT">
<approach speed="47" aoa="6">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.5"/>
</approach>
<cruise speed="153" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.9"/>
</cruise>
<rotor name="main" x="-2.75" y="0.0" z="1.55" nx="0.087" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
maxcollective="14.4" mincollective="-0.7"
mincyclicele="-12.1" maxcyclicele="6.18"
mincyclicail="-5.22" maxcyclicail="6.7"
diameter="11"
numblades="4"
weightperblade="75"
relbladecenter="0.5"
dynamic="0.82"
rpm="383"
rellenflaphinge="0.18"
delta3="0"
phi0="45"
delta=".125"
pitch-a="10"
pitch-b="15"
flapmin="-15"
flapmax="15"
flap0="-5"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="20"
translift-maxfactor="1.5"
ground-effect-constant="0.1"
twist="-10"
taper="1"
chord="0.32"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.076"
airfoil-lift-coefficient="4.6"
airfoil-drag-coefficient0="0.0074"
airfoil-drag-coefficient1="0.05"
incidence-stall-zero-speed="16"
incidence-stall-half-sonic-speed="15.5"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="2.0"
cyclic-factor="0.8"
rotor-correction-factor="0.95"
downwashfactor="0.6"
>
<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL"/>
<control-input axis="/controls/flight/fcs/roll" control="CYCLICAIL"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/elevator-trim" control="CYCLICELE"/>
<control-input axis="/controls/flight/fcs/pitch" control="CYCLICELE"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE"
src0="0.0" src1="1.0"
dst0="1.0" dst1="-1"/>
</rotor>
<rotor name="tail" x="-9.224" y="0.18" z="1.69" nx="0.07" ny="-1" nz="-0.05" fx="1" fy="0" fz="0" ccw="1"
maxcollective="13.6" mincollective="-9"
phi0="110"
diameter="1.91" numblades="2" weightperblade="2" relbladecenter="0.7"
dynamic="1" rpm="2168" rellenflaphinge="0.0" delta3="1" translift="0" delta="0.5"
sharedflaphinge="1"
flap0="-0.5"
pitch-a="10"
pitch-b="15"
airfoil-lift-coefficient="6.4"
airfoil-drag-coefficient0="0.0035"
airfoil-drag-coefficient1="0.10"
notorque="0"
taper="1"
chord="0.25"
number-of-segments="5"
number-of-parts="4"
rel-len-blade-start="0.33"
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"
rotor-correction-factor="1.0"
downwashfactor="1.0"
>
<control-input axis="/controls/flight/fcs/yaw" control="COLLECTIVE" invert="true"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/fcs/tail-rotor/throttle" control="COLLECTIVE"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
</rotor>
<rotorgear
max-power-engine="1100"
max-power-rotor-brake="100"
rotorgear-friction="1.4"
engine-prop-factor="0.005"
engine-accel-limit="4"
yasimdragfactor="18.5"
yasimliftfactor="18">
>
<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="1.0"
dst0="0.0" dst1="1.0"/>
</rotorgear>
<cockpit x="-1.88" y=".33" z="0.6"/>
<fuselage ax="-.65" ay="0" az="-.07" bx="-5.05" by="0" bz="-.07" cx="2.0"
width="1.92" taper="0.95" midpoint="0.5" idrag="0"/>
<fuselage ax="-5.05" ay="0" az="-.38" bx="-8.40" by="0" bz=".51" cz="0.25" cx="1"
width="0.47" taper="0.9" midpoint="0.05" idrag="0.0"/>
<vstab x="-8.4" y="0" z=".69" taper=".5" length="1.37" chord=".59" sweep="40">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.74" y="1.27" z=".0" taper="1" length=".65" chord=".40" sweep="8">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.74" y="-1.27" z=".0" taper="1" length=".65" chord=".40" sweep="8">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<hstab x="-7.5" y="0.05" z="-0.64" taper="1.0" effectiveness="2.0" length="1.20" chord="0.36" sweep="0" incidence="-2">
<stall aoa="0" width="0" peak="1.5"/>
</hstab>
<!-- left skid -->
<gear x="-1.24" y="+1.30" z="-1.65" skid="1" compression="0.20" spring="1.6" sfric="0.5" dfric="0.4"/>
<gear x="-3.52" y="+1.30" z="-1.65" skid="1" compression="0.1" spring="1.6" sfric="0.5" dfric="0.4"/>
<!-- right skid -->
<gear x="-1.24" y="-1.30" z="-1.65" skid="1" compression="0.20" spring="1.6" sfric="0.5" dfric="0.4"/>
<gear x="-3.52" y="-1.30" z="-1.65" skid="1" compression="0.1" spring="1.6" sfric="0.5" dfric="0.4"/>
<!-- tail skid -->
<gear x="-8.893" y="+0.00" z="-0.034" skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"/>
<tank x="-2.69" y="0" z=".68" capacity="1006"/> <!-- main: 580 l (570 l usable) @ 6.682 ppg (H3EU.pdf) -->
<tank x="-1.74" y="0" z=".68" capacity="163.7"/> <!-- supply: 93 l (usable?) -->
<ballast x="-2.90" y="+0.0" z="0.2" mass="600"/>
<ballast x="-4.0" y="+0.0" z="0.5" mass="300"/>
<ballast x=" -3.5" y="-2.25" z="1.0" mass="150"/>
<ballast x="-3.5" y="+2.25" z="1.0" mass="150"/>
<ballast x="-3.6" y="0" z="1.50" mass="200"/>
<ballast x="-3.6" y="0" z="-1.50" mass="200"/>
<ballast x="-0.4" y="+0.0" z="-0.8" mass="800"/>
<ballast x="1.0" y="0" z=".68" mass="182"/>
<ballast x="-4.0" y="0" z=".68" mass="-182"/>
<weight x="-1.0" y=".33" z="1" mass-prop="/sim/weight[0]/weight-lb"/> <!-- pilot -->
<weight x="-1.0" y="-.33" z="1" mass-prop="/sim/weight[1]/weight-lb"/> <!-- co-pilot -->
<weight x="-2.0" y=".33" z="1" mass-prop="/sim/weight[2]/weight-lb"/> <!-- right passenger -->
<weight x="-2.0" y="0" z="1" mass-prop="/sim/weight[3]/weight-lb"/> <!-- middle passenger -->
<weight x="-2.0" y="-.33" z="1" mass-prop="/sim/weight[4]/weight-lb"/> <!-- left passenger -->
<weight x="-3.5" y="0" z="1" mass-prop="/sim/weight[5]/weight-lb"/> <!-- patient/load -->
<thruster x="-2.55" y="0.0" z="1.55" vx="1" vy="0" vz="0" thrust="4000">
<control-input axis="/rotors/main/vibration/longitudinal" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>
<thruster x="-2.55" y="0.0" z="1.55" vx="0" vy="1" vz="0" thrust="4000">
<control-input axis="/rotors/main/vibration/lateral" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>
<thruster x="-2.38" y="0" z="0" vx="0" vy="0" vz="1" thrust="2500">
<control-input axis="/gear/antislide" src0="0" src1="1" dst0="0" dst1="1" control="THROTTLE"/>
</thruster>
</airplane>