ch53e.xml

<?xml version="1.0" encoding="UTF-8"?>
<!-- This FDM is based on Josh Babcock's CH-53E original one. Most of the values in 
the "MainRotor","TailRotor","RotorGear" & Fuel tanks capacity have not been changed -->

<airplane mass="33228" version="YASIM_VERSION_CURRENT">

	<approach speed="60" aoa="16">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
	</approach>

	<cruise speed="170" alt="0">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
	</cruise>



<rotor name="main"
		 x="-0.057" y="0.0"    z="3.528"
		nx="0.085"  ny="-0.00" nz="1.0"
		fx="1"     fy="0"     fz="0"
		diameter="24.079" rel-len-blade-start="0.29"
      chord="0.744" twist="-14"
      numblades="7" weightperblade="600" relbladecenter="0.61"
      rel-len-where-incidence-is-measured="0.55"

			maxcollective="33.6" mincollective="-5.5"
		mincyclicele="-29.05" maxcyclicele="21"
		mincyclicail="-8.8" maxcyclicail="14.7"


		flapmin="-18" flapmax="18" flap0="-5"
		delta="0.5" rellenflaphinge="0.063" delta3="0"
		phi0="0.0"

		airfoil-incidence-no-lift="-0.75"
		airfoil-lift-coefficient="6.3"
		airfoil-drag-coefficient0="0.0085"
		airfoil-drag-coefficient1="0.03"
		lift-factor-stall="0.18"
		stall-change-over="3"
		drag-factor-stall="2.0"
		cyclic-factor="0.8"
		rotor-correction-factor="0.85"

		incidence-stall-zero-speed="18"
		incidence-stall-half-sonic-speed="14.5"
		translift-ve="20"
		translift-maxfactor="1.3"
		ground-effect-constatnt="1.20"

		dynamic="1.4" number-of-segments="8" number-of-parts="8"
		rpm="177" ccw="1" balance="0.998" notorque="0" >
	
		<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="1"/>
		<control-input axis="/controls/flight/aileron" control="CYCLICAIL"/>	
	
		<control-input axis="/controls/flight/elevator-trim" control="CYCLICELE" split="1"/> 
		<control-input axis="/controls/flight/elevator" control="CYCLICELE"/>
	
		<control-input axis="/controls/engines/engine[0]/throttle" invert="1" control="COLLECTIVE"/>
	</rotor>
	
	
	
	<rotor name="tail" x="-15.194" y="1.716" z="4.314" nx="0.0" ny="-0.99" nz="0.36" fx="1" fy="0" fz="0"
		diameter="6.096" rel-len-blade-start="0.1"
      chord="0.39" twist="-8"
		numblades="4" weightperblade="100" relbladecenter="0.58"
      rel-len-where-incidence-is-measured="0.7"

		maxcollective="17.47" mincollective="-5"

		flapmin="-8" flapmax="8" flap0="0" flap0factor="0"
		delta="0.5" rellenflaphinge="0.043" delta3="1"

		incidence-stall-zero-speed="15.5"
		incidence-stall-half-sonic-speed="15.5"
		lift-factor-stall="0.5"
		drag-factor-stall="3.5"
		stall-change-over="3.0"
		translift-ve="20"
		translift="0"

		airfoil-lift-coefficient="5.7"
		airfoil-drag-coefficient0="0.0074"
		airfoil-drag-coefficient1="0.045"
		rotor-correction-factor="0.8"

		dynamic="1.0" number-of-segments="5" number-of-parts="4"
		rpm="700" ccw="1" balance="0.998" notorque="0" >
	
		<control-input axis="/controls/flight/rudder" control="COLLECTIVE" invert="1"/>
		<control-input axis="/controls/engines/engine[0]/throttle" invert="1" control="COLLECTIVE"
			src0="0" dst0="-0.05"
			src1="1" dst1="+0.23"/>
	</rotor>
	
	
	
    <!-- Need max speed at given weights to get the drag factor right -->
    <!--3 off General Electric T64-GE-416/416A turboshaft, 4,380 shp(3,270 kW) each -->
	<rotorgear
		max-power-engine="9810"
		max-power-rotor-brake="600"
		rotorgear-friction="1.5"
		engine-prop-factor="0.03"
		engine-accel-limit="1.96"
		yasimdragfactor="53"
		yasimliftfactor="165" >
		<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
		<control-input axis="/controls/rotor/brake" control="ROTORBRAKE"/>
	</rotorgear>	
	

	<cockpit x="4.997" y="-0.6" z="1.395"/>
<!-- FuselageMain -->
    <fuselage ax="6.525" ay="0" az="0.238" bx="4.217" by="0" bz="0.566" width="2.77" taper="0.5" midpoint="1.0"  cz="0.2" idrag="0"/>
	 
	<fuselage ax="4.426" ay="0" az="0.566" bx="-5.10" by="0" bz="0.566" width="2.77" taper="1.0" midpoint="0.5"  cz="0.2" idrag="0"/>

	<fuselage ax="-4.861" ay="0" az="0.566" bx="-11.014" by="0" bz="1.493" width="2.77" taper="0.3" midpoint="0.0"  cz="0.2" idrag="0"/>
    
	<fuselage ax="-10.947" ay="0" az="1.493" bx="-14.053" by="0" bz="1.493" width="0.82" taper="1.0" midpoint="0.0"  cz="0.2" idrag="0"/>
    
	<fuselage ax="2.880" ay="1.909" az="-0.152" bx="-3.927" by="1.909" bz="-0.152" width="1.0" taper="0.8" midpoint="0.5"  cz="0.2" idrag="0"/>
	
	<fuselage ax="2.880" ay="-1.909" az="-0.152" bx="-3.927" by="-1.909" bz="-0.152" width="1.0" taper="0.8" midpoint="0.5"  cz="0.2" idrag="0"/>
	
	<fuselage ax="2.880" ay="3.026" az="-0.152" bx="-3.985" by="3.026" bz="-0.152" width="0.8" taper="0.7" midpoint="0.5"  cz="0.2" idrag="0"/>
	
	<fuselage ax="2.880" ay="-3.026" az="-0.152" bx="-3.985" by="-3.026" bz="-0.152" width="0.8" taper="0.7" midpoint="0.5"  cz="0.2" idrag="0"/>
	
    <!-- probe -->
	<fuselage ax="9.850" ay="-.975" az="-0.1" bx="4.3" by="-.975" bz="-0.1" width="0.4" taper=".25" midpoint="1.0" idrag="0"/>

    <!-- fuselage top -->
	<fuselage ax="4.426" ay="0" az="2.0" bx="-6.0" by="0" bz="2.0" width="2.0" taper=".5" midpoint="0.5" idrag="0"/>

    <!-- fuselage right engine -->
	<fuselage ax="4.0" ay="1.7" az="2.0" bx="-0.5" by="1.7" bz="2.0" width="1.25" taper=".5" midpoint="0.25" idrag="0"/>

    <!-- fuselage left engine -->
	<fuselage ax="4.0" ay="-1.7" az="2.0" bx="-0.5" by="-1.7" bz="2.0" width="1.25" taper=".5" midpoint="0.25" idrag="0"/>

    <!-- fuselage engine #3 -->
	<fuselage ax=".4" ay="1.0" az="2.5" bx="-1.9" by="1.0" bz="2.5" width="1.25" taper=".5" midpoint="0.5" idrag="0"/>

	<!--Rudder -->	
	<vstab x="-13.253" y="0" z="1.9" taper="0.75" dihedral="70" length="4.01" chord="1.85" sweep="33"
		camber="0.2" effectiveness="0.9">
		<stall aoa="16" width="4" peak="1.5"/>
	</vstab>

	<!-- horizontal stabilizer on right side -->
    <!-- note: use unmirrored vstab with dihedral of 0 degrees (all other surfaces are mirrored) -->
    <vstab x="-15.2" y="-3.315" z="4.6"
        taper="1.0"
        length="2.2"
        chord="1.081"
        camber="0"
        sweep="0"
        dihedral="0"
        effectiveness="0.5">
		<stall aoa="0" width="0" peak="1.5"/>
    </vstab>
  
<!-- nose gear -->
<gear x="5.797" y="0.00" z="-1.47" compression="0.4" sfric="1.5" dfric="0.8"  retract-time="5"
    spring="2.3" damp="1.0" initial-load="0">
    <control-input axis="/controls/flight/rudder" control="STEER" square="true"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="6"/>
    <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
  </gear>

	<!-- right gear -->
<gear x="-2.497" y="-1.98" z="-1.48" compression="0.4" sfric="1.5" dfric="0.8" retract-time="5"
    spring="1.7" damp="1.0" initial-load="0">
    <control-input axis="/controls/gear/brake-right" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="6"/>
    <control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
  </gear>
  
  <!-- left gear -->
<gear x="-2.497" y="1.98" z="-1.48" compression="0.4" sfric="1.5" dfric="0.8"  retract-time="5"
    spring="1.7" damp="1.0" initial-load="0">
    <control-input axis="/controls/gear/brake-right" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="6"/>
    <control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
  </gear>



	<!-- tail gear ( Simulates the tail boom here) -->
<gear x="-13.344" y="0" z="0.0" compression="0.2" sfric="1.5" dfric="0.8" retract-time="4.9"
    spring="1.3" damp="1.0" initial-load="0">
   
  </gear>



 <!-- Fuel Tanks -->
	
	<tank x="-0.552" y="3.026" z="-0.148" capacity="4368" jet="true"/>
	<tank x="-0.194" y="1.909" z="-0.148" capacity="2200" jet="true"/> 
	<tank x="1.564" y="1.909" z="-0.148" capacity="1400" jet="true"/>
	<tank x="-0.552" y="-3.026" z="-0.148" capacity="4368" jet="true"/>
	<tank x="-0.194" y="-1.909" z="-0.148" capacity="2200" jet="true"/> 
	<tank x="1.564" y="-1.909" z="-0.148" capacity="1400" jet="true"/>

<!-- ballast -->
    <!-- Leftt -->
	<ballast x="2.060" y="1.106" z=" -0.546" mass="3360"/>
	<ballast x="-1.934" y="1.106" z=" -0.546" mass="2500"/>

	<!-- Middle -->
	<ballast x="2.060" y="0.0" z=" -0.546" mass="6360"/>
	<ballast x="-1.934" y="0.0" z=" -0.546" mass="5500"/>

	<!-- Right -->	
	<ballast x="2.060" y="-1.106" z=" -0.546" mass="3360"/>
	<ballast x="-1.934" y="-1.106" z=" -0.546" mass="2500"/>

	

    <!-- pilot -->
	<weight x="4.933" y="0.594" z="0.867" mass-prop="/sim/weight[0]/weight-lb"/>
	<!-- co-pilot -->
	<weight x="4.933" y="-0.594" z="0.867" mass-prop="/sim/weight[1]/weight-lb"/>
	<!-- aircrewman1 -->
	<weight x="2.474" y="0.806" z="-0.026" mass-prop="/sim/weight[2]/weight-lb"/>
    <!-- aircrewman2 -->
	<weight x="2.474" y="-0.806" z="-0.026" mass-prop="/sim/weight[3]/weight-lb"/>

    <!-- payload -->
    <!-- utility hoist -->
    <weight x="3.634" y="-1.849" z="1.172" mass-prop="/sim/weight[4]/weight-lb"/>
    <!-- internal -->
    <weight x="0.0" y="0.0" z=".5" mass-prop="/sim/weight[5]/weight-lb"/>
    <!-- fore hook-->
    <weight x="1.379" y="0.0" z="-0.546" mass-prop="/sim/weight[6]/weight-lb"/>
    <!-- center hook -->
    <weight x="-0.662" y="0.0" z="-0.546" mass-prop="/sim/weight[7]/weight-lb"/>
    <!-- aft hook -->
    <weight x="-2.0" y="0.0" z="-0.546" mass-prop="/sim/weight[8]/weight-lb"/>

</airplane>