ec145/extras/ec145.xml

<!-- 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>