<!--
Syd Adams, Josh Babcock, Maik Justus
NOTES:
Blades (fiberglass)
-12 degree twist
32 inch chord
weight ?
Frt Rotor hub 9 degree forward pitch
Rr Rotor hub 4 degree forward pitch
-->
<airplane mass="23500">

	<!-- Approach configuration, only for gear solver :-)  -->
	<approach speed="70" aoa="0" alt="0">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="0.05"/>
	</approach>

	<!-- Cruise configuration, only for gear solver :-)  -->
	<cruise speed="70" aoa="0" alt="0">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
	</cruise>

	<rotor
	name="main"
	x="5.6"
	y="0.0"
	z="2.4"
	nx="0.15"
	ny="0"
	nz="1"
	fx="1"
	fy="0"
	fz="0"
	ccw="0"
	maxcollective="100.0"
	mincollective="-100.0"
	mincyclicele="-100.0"
	maxcyclicele="100.0"
	mincyclicail="-100"
	maxcyclicail="100"
	diameter="18.29"
	numblades="3"
	weightperblade="357"
	relbladecenter="0.53"
	dynamic="1.0"
	rpm="225"
	rellenflaphinge="0.03"
	delta3="0"
	delta="0.2"
	pitch-a="10"
	pitch-b="15"
	flapmin="-18"
	flapmax="18"
	flap0="-9"
	flap0factor="0"
	notorque="0"
	dragfactor="0.30"
	translift-ve="20"
	translift-maxfactor="1.3"
	ground-effect-constant="0.1"
	twist="-12.0"
	taper="1"
	chord="0.8128"
	number-of-segments="8"
	number-of-parts="8"
	rel-len-where-incidence-is-measured="0.7"
	rel-len-blade-start="0.12"
	tiltcenterx="5.6"
	tiltcentery="0"
	tiltcenterz="2.4"
	mintiltyaw="0"
	mintiltpitch="-9"
	mintiltroll="0"
	maxtiltyaw="0"
	maxtiltpitch="9"
	maxtiltroll="0"
	downwashfactor="0.3"
	airfoil-lift-coefficient="5.7"
	airfoil-drag-coefficient0="0.0075"
	airfoil-drag-coefficient1="0.045"
	incidence-stall-zero-speed="10.5"
	incidence-stall-half-sonic-speed="10.5"
	lift-factor-stall="0.2"
	stall-change-over="5.5"
	drag-factor-stall="35.0"
	cyclic-factor="0.8"
	rotor-correction-factor="0.85">

		<control-input axis="controls/flight/rudder" control="CYCLICAIL"
		   src0="-1.0" src1="1.0"
		   dst0="-0.02" dst1="0.02"/>
		<control-input axis="controls/flight/aileron" control="CYCLICAIL"
		   src0="-1.0" src1="1.0"
		   dst0="-0.02" dst1="0.02"/>
		<control-input axis="controls/flight/elevator" control="COLLECTIVE"
		   src0="-1.0" src1="1.0"
		   dst0="0.02" dst1="-0.03"/>
		<control-input axis="controls/engines/engine[1]/throttle" control="COLLECTIVE"
		   src0="-0.0" src1="1.0"
		   dst0="0.12" dst1="0.01"/>
		<control-input axis="controls/rotor/pitch" control="TILTPITCH"
			   src0="0.0" src1="1.0"
		dst0="0" dst1="-1.0"/>
	</rotor>

	<rotor
	name="main2"
	x="-5.6"
	y="0.0"
	z="3.7"
	nx="0.07"
	ny="0"
	nz="1.0"
	fx="1"
	fy="0"
	fz="0"
	ccw="1"
	maxcollective="100"
	mincollective="-100.0"
	mincyclicele="-100.0"
	maxcyclicele="100.0"
	mincyclicail="-100.0"
	maxcyclicail="100.0"
	diameter="18.29"
	numblades="3"
	weightperblade="357"
	relbladecenter="0.53"
	dynamic="1.0"
	rpm="225"
	rellenflaphinge="0.03"
	delta3="0"
	delta="0.2"
	pitch-a="10"
	pitch-b="15"
	flapmin="-18"
	flapmax="18"
	flap0="-9"
	flap0factor="0"
	notorque="0"
	dragfactor="0.30"
	translift-ve="20"
	translift-maxfactor="1.3"
	ground-effect-constant="0.1"
	twist="-12.0"
	taper="1"
	chord="0.8128"
	number-of-segments="8"
	number-of-parts="8"
	rel-len-where-incidence-is-measured="0.7"
	rel-len-blade-start="0.12"
	tiltcenterx="-5.6"
	tiltcentery="0"
	tiltcenterz="3.7"
	mintiltyaw="0"
	mintiltpitch="-4"
	mintiltroll="0"
	maxtiltyaw="0"
	maxtiltpitch="4"
	maxtiltroll="0"
	downwashfactor="0.3"
	airfoil-lift-coefficient="5.7"
	airfoil-drag-coefficient0="0.0075"
	airfoil-drag-coefficient1="0.045"
	incidence-stall-zero-speed="10.5"
	incidence-stall-half-sonic-speed="10.5"
	lift-factor-stall="0.2"
	stall-change-over="5.5"
	drag-factor-stall="35.0"
	cyclic-factor="0.8"
	rotor-correction-factor="0.85">

		<control-input axis="controls/flight/rudder"
		control="CYCLICAIL"
		invert="true"
		src0="-1.0" src1="1.0"
		dst0="-0.02" dst1="0.02"/>
		<control-input axis="controls/flight/aileron"
		control="CYCLICAIL"
		src0="-1.0" src1="1.0"
		dst0="-0.02" dst1="0.02"/>
		<control-input axis="controls/flight/elevator"
		control="COLLECTIVE"
		src0="-1.0" src1="1.0"
		dst0="-0.03" dst1="0.02"/>
		<control-input axis="controls/engines/engine[1]/throttle"
		control="COLLECTIVE"
		src0="-0.0" src1="1.0"
		dst0="0.12" dst1="0.01"/>
		<control-input axis="controls/rotor/pitch"
		control="TILTPITCH"
		src0="-1.0" src1="1.0"
		dst0="1.0" dst1="-1.0"/>
	</rotor>
	<rotorgear
	max-power-engine="7258"
	max-power-rotor-brake="100"
	rotorgear-friction="257"
	engine-prop-factor="0.005"
	engine-accel-limit="2"

	yasimdragfactor="280"
	yasimliftfactor="251"
>
		<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"/>
	</rotorgear>




	<!--cockpit x="-1.88" y="0" z="0.6"/-->
	<cockpit x="6.0" y="0" z="0.5"/>


	<!-- main body -->
	<!-- README.yasim says "taper" is fraction of "radius". ...not width?? -->
	<fuselage ax="6.6" ay="0" az="0.6" bx="-3.4" by="0" bz="0.6" idrag="0"
	width="1.25" taper="1" midpoint="0.5" cz="0.2" cy="1" cx="0.15"/>
	<fuselage ax="6.6" ay="0" az="-0.6" bx="-3.4" by="0" bz="-0.6" idrag="0"
	width="1.25" taper="1" midpoint="0.5" cz="0.2" cy="1" cx="0.15"/>

	<!-- left engine, x uncertain -->
	<!-- 
<fuselage ax="-3.6" ay="1.22" az="1.68" bx="-5.9" by="1.22" bz="1.68"
width="0.8" taper="1" midpoint="0.5" cz="0.3" cy="3" cx="10"/>
-->
	<!-- right engine -->
	<!--
<fuselage ax="-3.6" ay="-1.22" az="1.68" bx="-5.9" by="-1.22" bz="1.68"
width="0.8" taper="1" midpoint="0.5" cz="0.3" cy="3" cx="10"/>
-->

	<!-- Aerodynamic effect of the fuel tank sidesteps? And what about the
swept up stern? Is the fwd pylon a h+vstab or a pure drag element? -->

	<!-- fueltanks sidesteps as drag -->

	<fuselage ax="3.6" ay="1.5" az="-0.5" bx="-4.4" by="1.5" bz="-0.5" idrag="0"
	width="1.8" taper="1.0" midpoint="0.5" cx="0.15" cz="0.2"/>
	<fuselage ax="3.6" ay="-1.5" az="-0.5" bx="-4.4" by="-1.5" bz="-0.5" idrag="0"
	width="1.8" taper="1.0" midpoint="0.5" cx="0.15" cz="0.2"/>

	<!--
	<fuselage ax="-6.6" ay="2" az="0.6" bx="-3.4" by="2" bz="0.6"
	width="1.25" taper="1.0" midpoint="0.5" cx="10" cz="0.3 idrag="0""/>
	<fuselage ax="-6.6" ay="-2" az="-0.6" bx="-3.4" by="-2" bz="-0.6"
	width="1.25" taper="1.0" midpoint="0.5" cx="10" cz="0.3" idrag="0"/>
	-->
	<!-- tail shape (and rotor downwash on hull) as a small horisontal stabiliser (downforce) -->
	<!-- mstab x="-6.4" y="0" z="0" taper="1" length="2.0" chord="1" camber="-0.15"
incidence="-3" > <stall aoa="20" /> </mstab -->

	<!-- fwd pylon, as drag -->
	<!--
	<fuselage ax="-6.4" ay="0" az="1.8" bx="-4.6" by="0" bz="1.8" idrag="0"
	width="1.0" taper="0.1" midpoint="0.3"/>
	-->
	<!-- aft pylon, as a vstab -->
	<vstab x="-5.4" y="0" z="1" taper="0.9"
	length="2.5" chord="4.5" sweep="0">
		<stall aoa="30" width="20" />
	</vstab>
	<!-- aft pylon, as drag -->
	<fuselage ax="-3.4" ay="0" az="2.5" bx="-5.9" by="0" bz="2.5"
	width="1.0" taper="0.2" midpoint="0.4" cy="3" cx="10" idrag="0"/>

	<gear x="2.78" y="-1.5" z="-2.0"
	compression="0.5"
	spring="10.5"
	damp="1.0">
		<control-input axis="controls/flight/rudder" control="STEER" square="true"/>
		<control-input axis="controls/gear/brake-left" control="BRAKE"/>
		<control-input axis="controls/gear/brake-parking" control="BRAKE"/>
	</gear>

	<gear x="2.78" y="1.5" z="-2.0"
	compression="0.5"
	spring="10.5"
	damp="1.0">
		<control-input axis="controls/flight/rudder" control="STEER" square="true"/>
		<control-input axis="controls/gear/brake-right" control="BRAKE"/>
		<control-input axis="controls/gear/brake-parking" control="BRAKE"/>
	</gear>

	<gear x="-4.45" y="1.5" z="-1.7"
	compression="0.5"
	spring="10.5"
	damp="1.0">
		<control-input axis="controls/gear/brake-left" control="BRAKE"/>
		<control-input axis="controls/gear/brake-parking" control="BRAKE"/>
	</gear>

	<gear x="-4.45" y="-1.5" z="-1.7"
	compression="0.5"
	spring="10.5"
	damp="1.0">
		<control-input axis="controls/gear/brake-right" control="BRAKE"/>
		<control-input axis="controls/gear/brake-parking" control="BRAKE"/>
	</gear>


	<!--two main tanks 1034 gal total-->

	<tank x="0" y="1.5" z="-0.5" capacity="3464"/>
	<tank x="0" y="-1.5" z="-0.5" capacity="3464"/>

	<tank x="0" y="0" z="0" capacity="0"/>


	<ballast x="5.6" y="-0.33" z="0" mass="180"/>
	<!-- pilot -->
	<ballast x="5.6" y="0.33" z="0" mass="180"/>
	<!-- copilot -->
	<ballast x="6.6" y="-.0" z="0" mass="200"/>
	<!-- cockpit -->

	<!-- left engine, x is estimated -->
	<ballast x="-4.4" y="1.22" z="1.68" mass="640" />
	<!-- right engine -->
	<ballast x="-4.4" y="-1.22" z="1.68" mass="640" />

	<ballast x="2.6" y="0" z="0" mass="9000"/>
	<!-- Yasim bug kludge-->
	<ballast x="-4.4" y="0" z="0" mass="9000"/>
	<!-- Yasim bug kludge-->
	<ballast x="1" y="0" z="0" mass="2000"/>
	<!-- Trim ballast -->
	<weight x="0" y="0" z="0" mass-prop="/sim/weight[0]/weight-lb"/>
	<!-- inner payload -->

	<!-- some ballast to get c.g. correct and inertia tensor reasonable
	   (max fwd cg at x=0.1, max aft cg at x=-0.6, cg (empty) at x=-0.5)
	-->
	<ballast x="0" y="0.0" z="-0.5" mass="3000"/>
	<ballast x="0" y="-3.0" z="-3.0" mass="3000"/>
	<ballast x="0" y="+3.0" z="3.0" mass="3000"/>
	<ballast x="0" y=" 0.0" z="-3.0" mass="3000"/>
	<ballast x="-4.6" y=" 0.0" z="+3.0" mass="3000"/>


</airplane>