<?xml version="1.0"?>
<!--

************************************************************************

YASim aerodynamic model for a Hurricane IIb

Sources: 

	Hurricane Mk II Performance
	Aeroplane and Armament Experimental Establishment 
	Boscombe Down 
	21st October 1941

 
	NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
	WARTIME REPORT
	ORIGINALLY ISSUED
	April 1942 as
	Memorandum Report

	MEASUREMENT OF THE FLYING QUALITIES OF
	A HAWKER HURRICANE AIRPLANE

	by J M.Nissen and W. H. Phillips
	Langley Field Memorial Aeronautical Laboratory
	Langley Field, Va.
	NACA
	WASHINGTON

This configuration has been developed with a great deal of assistance
by Emilian Huminiuc and includes many of his ideas and suggestions for
improvements. He has also contributed many hours testing to tune the
results.

© Vivian Meazza & Emilian Huminiuc 2012

The reference datum for measurements is the nose.

************************************************************************

-->
<!-- Weight of everything but fuel  (5590lbs empty) -->
<airplane mass="6464">

	<!-- Approach configuration -->
	<approach speed="61"
						aoa="12">
		<control-setting axis="/controls/engines/engine[0]/throttle"
										 value="0.3"/>
		<control-setting axis="/controls/engines/engine[0]/boost-control"
										 value="0.0"/>
		<control-setting axis="/controls/engines/engine[0]/mixture"
										 value="1.0"/>
		<control-setting axis="/controls/engines/engine[0]/propeller-pitch"
										 value="1"/>
		<control-setting axis="/controls/engines/engine[0]/boost"
										 value="0.633"/>
		<!--<control-setting axis="/controls/flight/flaps"
										 value="1.0"/>-->
		<control-setting axis="/systems/hydraulic/outputs/flaps"
										 value="1.0"/>
		<!--<control-setting axis="/controls/gear/gear-down"
										 value="1"/>-->
		<control-setting axis="systems/hydraulic/outputs/gear[1]"
										 value="1.0"/>
		<control-setting axis="systems/hydraulic/outputs/gear[2]"
										 value="1.0"/>
		<control-setting axis="/controls/flight/canopy-slide"
										 value="0.0"/>
		<solve-weight idx="0"
									weight="200"/>
	</approach>

	<!-- Cruise configuration -->
	<cruise speed="213"
					alt="20800"
					fuel="0.9">
		<control-setting axis="/controls/engines/engine[0]/throttle"
										 value="1.0"/>
		<control-setting axis="/controls/engines/engine[0]/boost-control"
										 value="0.0"/>
		<control-setting axis="/controls/engines/engine[0]/mixture"
										 value="1.0"/>
		<control-setting axis="/controls/engines/engine[0]/propeller-pitch"
										 value="1.0"/>
		<control-setting axis="/controls/engines/engine[0]/boost"
										 value="1.0"/>
		<control-setting axis="/controls/hydraulic/outputs/flaps"
										 value="0.0"/>
		<!--<control-setting axis="/controls/gear/gear-down"
										 value="0"/>-->
		<control-setting axis="systems/hydraulic/outputs/gear[1]"
										 value="0.0"/>
		<control-setting axis="systems/hydraulic/outputs/gear[2]"
										 value="0.0"/>
		<control-setting axis="/controls/flight/canopy-slide"
										 value="0.0"/>
		<solve-weight idx="0"
									weight="200"/>
	</cruise>

	<!-- pilot's eyepoint -->
	<cockpit x="-3.86"
					 y="0"
					 z="0.55"/>

	<!-- Fuselage -->
	<fuselage
		ax="0.0"
		ay="0.0"
		az="0.0"
		bx="-0.65"
		by="0.0"
		bz="0.0"
		width="0.6"
		taper="0.2"
		midpoint="1"
		/>
	<fuselage
		ax="-0.65"
		ay="0.0"
		az="0.0"
		bx="-1.968"
		by="0.0"
		bz="-0.10"
		cx="0.5"
		width="1.255"
		taper="0.47"
		midpoint="1"
		/>
	<fuselage
		ax="-1.968"
		ay="0.0"
		az="-0.10"
		bx="-5.3"
		by="0.0"
		bz="-0.10"
		cx="0.5"
		width="1.255"
		taper="1"
		midpoint="1"
		/>
	<fuselage
		ax="-5.3"
		ay="0.0"
		az="-0.10"
		bx="-9.11"
		by="0.0"
		bz="-0.10"
		cx="0.4"
		width="1.255"
		taper="0.58"
		midpoint="0"
				/>

	<!-- stub wing  -->
	<mstab x="-3.76"
				 y="0.44"
				 z="-0.58"
				 taper="0.81"
				 incidence="2"
				 twist="0"
				 chord="3.08"
				 sweep="-17.25"
				 length="0.942"
				 camber="0.065"
				 idrag="1.2"
				>
		<stall aoa="24.5"
					 width="20.5"
					 peak="1.72"/>
		<flap0 start="0.00"
					 end="1"
					 lift="1.5"
					 drag="1.545"/>
		<control-input axis="/systems/hydraulic/outputs/flaps"
									 control="FLAP0"/>
		<control-output control="FLAP0"
										prop="/surface-positions/flap-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="10"/>
	</mstab>

	<!-- wing, flaps section -->
	<wing x="-3.48"
				y="1.34"
				z="-0.57"
				taper="0.77"
				incidence="2.0"
				twist="-1.0"
				length="1.972"
				chord="2.497"
				sweep="-3"
				dihedral="3.5"
				camber="0.069"
				idrag="1.2"
				>
		<stall aoa="22"
					 width="23"
					 peak="1.81"/>
		<flap0 start="0.00"
					 end="1.0"
					 lift="1.8"
					 drag="1.75"/>
		<control-input axis="/systems/hydraulic/outputs/flaps"
									 control="FLAP0"
									 src0="0"
									 dst0="0"
									 src1="1"
									 dst1="1"/>
		<control-output control="FLAP0"
										prop="/surface-positions/flap-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="10"/>
	</wing>

	<!-- wing, left aileron section -->
	<vstab x="-3.381"
				 y="3.305"
				 z="-0.446"
				 taper="0.648"
				 incidence="1.0"
				 twist="-1.0"
				 length="2.344"
				 chord="1.926"
				 sweep="-3"
				 dihedral="3.5"
				 camber="0.0745"
				 idrag="1.2"
				>
		<stall aoa="17.5"
					 width="22.5"
					 peak="1.593"/>
		<flap0 start="0.00"
					 end="1.0"
					 lift="1.6"
					 drag="1.9"/>
		<control-input axis="/controls/flight/aileron-norm"
									 control="FLAP0"
									 src0="-1.0"
									 dst0="-0.92"
									 src1="1"
									 dst1="0.96"
									 />
		<control-input axis="/controls/flight/aileron-norm"
									 control="FLAP0EFFECTIVENESS"
									 src0="-1"
									 dst0="1.1"
									 src1="0"
									 dst1="1.0"
																		 />
		<control-input axis="/controls/flight/aileron-trim"
									 control="FLAP0"
									 src0="-1.0"
									 dst0="-0.92"
									 src1="1"
									 dst1="0.96"
																		 />
		<control-output control="FLAP0"
										prop="/surface-positions/left-aileron-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="0.1"/>
	</vstab>

	<!-- wing, right aileron section -->
	<vstab x="-3.264"
				 y="-5.64"
				 z="-0.299"
				 taper="1.543"
				 incidence="0.0"
				 twist="1.0"
				 length="2.344"
				 chord="1.248"
				 sweep="3"
				 dihedral="-3.5"
				 camber="0.0745"
				 idrag="1.2">
		<stall aoa="17.5"
					 width="22.5"
					 peak="1.593"/>
		<flap0 start="0.00"
					 end="1.0"
					 lift="1.6"
					 drag="1.9"/>
		<control-input axis="/controls/flight/aileron-norm"
									 control="FLAP0"
									 src0="-1.0"
									 dst0="0.86"
									 src1="1"
									 dst1="-1"
									/>
		<control-input axis="/controls/flight/aileron-norm"
									 control="FLAP0EFFECTIVENESS"
									 src0="0"
									 dst0="1.0"
									 src1="1.0"
									 dst1="1.1"
									/>
		<control-input axis="/controls/flight/aileron-trim"
									 control="FLAP0"
									 src0="-1.0"
									 dst0="0.86"
									 src1="1"
									 dst1="-1"
									/>
		<control-output control="FLAP0"
										prop="/surface-positions/right-aileron-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="0.1"/>
	</vstab>

	<!-- wing tip -->
	<mstab x="-3.264"
				 y="5.64"
				 z="-0.299"
				 taper="0.41"
				 incidence="0"
				 dihedral="3.5"
				 twist="0"
				 chord="1.248"
				 sweep="-0"
				 length="0.43"
				 camber="0.083"
				 idrag="1.2">
		<stall aoa="15"
					 width="20"
					 peak="4.38"/>
	</mstab>

	<!-- tailplane effectiveness="1.2"-->
	<hstab
		x="-8.899"
		y="0.08"
		z="0.224"
		taper="0.6"
		length="1.5"
		chord="1.382"
		sweep="-0.5"
		idrag="0.9">
		<stall aoa="12"
					 width="33"
					 peak="6.5"/>
		<flap0 start="0.0"
					 end="1.05"
					 lift="11"
					 drag="2.3"/>
		<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"/>
		<control-speed control="FLAP0"
									 transition-time="0.1"/>
	</hstab>

	<!-- tail -->
	<vstab x="-8.849"
				 y="0"
				 z="0.224"
				 taper="0.44"
				 effectiveness="1.0"
				 length="1.2"
				 chord="1.9"
				 sweep="15"
				 incidence="-1.5">
		<stall aoa="16.5"
					 width="28.5"
					 peak="6"/>
		<flap0 start="0"
					 end="1"
					 lift="5.3"
					 drag="1.5"/>
		<control-input axis="/controls/flight/rudder"
									 control="FLAP0"
									 invert="true"
									 square="true"/>
		<control-input axis="/controls/flight/rudder-trim"
									 control="FLAP0"
									 invert="true"/>
		<control-output control="FLAP0"
										prop="/surface-positions/rudder-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="0.1"/>
	</vstab>
	<vstab x="-8.849"
				 y="0"
				 z="-0.46"
				 taper="1.1875"
				 effectiveness="1.0"
				 length="0.684"
				 chord="1.6"
				 sweep="0"
				 incidence="-1.5">
		<stall aoa="16.5"
					 width="28.5"
					 peak="6"/>
		<flap0 start="0"
					 end="1"
					 lift="4.7"
					 drag="1.43"/>
		<control-input axis="/controls/flight/rudder"
									 control="FLAP0"
									 invert="true"
									 square="true"/>
		<control-input axis="/controls/flight/rudder-trim"
									 control="FLAP0"
									 invert="true"/>
		<control-output control="FLAP0"
										prop="/surface-positions/rudder-pos-norm"/>
		<control-speed control="FLAP0"
									 transition-time="0.1"/>
	</vstab>

	<!-- radiator 'wing' centre -->
	<mstab x="-3.93"
				 y="-0.0"
				 z="-1.09"
				 dihedral="0"
				 twist="0"
				 chord="1.00"
				 taper="1"
				 incidence="0"
				 sweep="0"
				 length="0.34"  >
		<stall aoa="25"
					 width="4"
					 peak="1.5"/>
		<flap0 start="0.00"
					 end="1"
					 lift="1.1"
					 drag="1.3"/>
		<control-input axis="/controls/engines/engine/rad-flap-norm"
									 control="FLAP0"/>
		<control-output control="FLAP0"
										prop="/engines/engine/rad-flap-norm"/>
		<control-speed control="FLAP0"
									 transition-time="3" />
	</mstab>

	<!-- propeller and engine -->
	<!-- moment = radius(m)* propeller mass(kg)/2 - equation provided by Andy Ross -->
	<!-- documented gear ratio of 0.477  min-rpm="1800" max-rpm="3000" takeoff-power="1280"
			takeoff-rpm="1431"
-->
	<propeller x="-1.35"
						 y="0"
						 z="-0.0"
						 mass="2055"
						 moment="60"
						 radius="1.638"
						 cruise-speed="223"
						 cruise-rpm="1260"
						 cruise-power="1480"
						 cruise-alt="13000"
						 min-rpm="715"
						 max-rpm="1260"
						 gear-ratio="0.42"
						 coarse-stop="2.1"
						 fine-stop="0.75"
						 takeoff-power="1400"
						 takeoff-rpm="1260">
		<actionpt x="-0.47"
							y="0"
							z="0"/>
		<dir x="1.0"
				 y="0"
				 z="0.009"/>
		<control-input axis="/controls/engines/engine[0]/propeller-pitch"
									 control="ADVANCE"/>
		<piston-engine
			eng-power="1480"
			eng-rpm="3000"
			displacement="1649"
			compression="6"
			turbo-mul="3.615"
			wastegate-mp="55"
			supercharger="1"
												>
			<control-input axis="/controls/engines/engine[0]/throttle"
										 control="THROTTLE"/>
			<control-input axis="/controls/engines/engine[0]/boost-control"
										 src0="-1"
										 src1="1"
										 dst0="-1"
										 dst1="1"
										 control="THROTTLE"/>
			<control-output control="THROTTLE"
											prop="/engines/engine/throttle-setting"/>
			<control-input axis="/controls/engines/engine[0]/starter"
										 control="STARTER"/>
			<control-input axis="/controls/engines/engine[0]/magnetos"
										 control="MAGNETOS"/>
			<control-input axis="/controls/engines/engine[0]/mixture"
										 control="MIXTURE"/>
			<control-input axis="/controls/engines/engine[0]/boost"
										 control="BOOST"/>
		</piston-engine>
	</propeller>

	<!-- simulate cannon recoil -->
	<thruster x="3.5"
						y="0"
						z="0.4"
						vx="-1"
						vy="0"
						vz="0.3"
						thrust="4000">
		<control-input axis="/sim/ai/recoil"
									 control="THROTTLE"
									 src0="0"
									 src1="1"
									 dst0="0"
									 dst1="1"/>
	</thruster>
	<thruster x="3.5"
						y="0"
						z="0.4"
						vx="1"
						vy="0"
						vz="-0.3"
						thrust="4000">
		<control-input axis="/sim/ai/runout"
									 control="THROTTLE"
									 src0="0"
									 src1="1"
									 dst0="0"
									 dst1="1"/>
	</thruster>

	<!-- Tail wheel -->
	<!-- tail wheel casters freely in Hurricane -->
	<gear x="-8.566"
				y="0"
				z="-0.946"
				compression="0.15"
				castering="1">
		<control-input axis="/controls/gear/tailwheel-lock"
									 src0="0"
									 src1="1"
									 dst0="1"
									 dst1="1"
									 control="CASTERING"/>
		<control-input axis="/controls/gear/brake-parking"
									 control="BRAKE"
									 transition-time="0"
									 src0="0"
									 src1="1.0"
									 dst0="0.4"
									 dst1="0.4"/>
	</gear>
	<!-- left main   dfric="0.5" sfric="0.6"dfric="0.5" sfric="0.6"-->
	<gear x="-2.76"
				y="1.18"
				z="-2.02"
				spring="1.2"
				damp="4.0"
				compression="0.25"
				dfric="0.7"
				sfric ="0.8">
		<control-input axis="/systems/pneumatic/outputs/brake"
									 control="BRAKE"
									 transition-time="0.25"
									 src0="0"
									 src1="1"
									 dst0="0.001"
									 dst1="0.6"/>
		<!--<control-input axis="/controls/gear/brake-parking"
									 control="BRAKE"
									 split="true"/>-->
		<control-input axis="/systems/hydraulic/outputs/gear[1]"
									 control="EXTEND"/>
		<control-speed control="EXTEND"
									 transition-time="9"/>
		<control-output control="EXTEND"
										prop="/gear/gear[1]/position-norm"/>
	</gear>
	<!-- right main spring="0.7" damp="3.0" -->
	<gear x="-2.76"
				y="-1.18"
				z="-2.02"
				spring="1.2"
				damp="4.0"
				compression="0.25"
				dfric="0.7"
				sfric ="0.8">
		<control-input axis="/systems/pneumatic/outputs/brake[1]"
									 control="BRAKE"
									 transition-time="0.25"
									 src0="0"
									 src1="1"
									 dst0="0.001"
									 dst1="0.6"/>
		<!--<control-input axis="/controls/gear/brake-parking"
									 control="BRAKE"
									 split="true"/>-->
		<control-input axis="systems/hydraulic/outputs/gear[2]"
									 control="EXTEND"/>
		<control-speed control="EXTEND"
									 transition-time="7"/>
		<control-output control="EXTEND"
										prop="/gear/gear[2]/position-norm"/>
	</gear>

	<!-- dummy Tail wheel - add a little friction to make it flyable! -->
	<gear x="-8.566"
				y="0"
				z="-0.946"
				compression="0.15"
				dfric="0.50"
				sfric ="0.60">
		<control-input axis="/controls/gear/brake-parking"
									 control="BRAKE"
									 transition-time="0"
									 src0="0"
									 src1="1"
									 dst0="0.4"
									 dst1="0.4"/>
	</gear>

	<!-- Canopy -->
	<gear x="-3.90"
				y="0.0"
				z="0.7"
				compression="1">
		<control-input axis="/controls/flight/canopy-slide"
									 control="EXTEND"/>
		<control-speed control="EXTEND"
									 transition-time="2"/>
		<control-output control="EXTEND"
										prop="/gear/canopy/position-norm"/>
	</gear>

	<!-- Hook
		<gear x="-6.70" y="0.0" z="-1.74" compression="1" spring="0.15">
			<control-input axis="/controls/gear/tailhook" control="EXTEND"/>
			<control-speed control="EXTEND" transition-time="2"/>
			<control-output control="EXTEND" prop="/gear/tailhook/position-norm"/>
		</gear>-->
	<!-- Hook  - the hook extends only - it has no retracting mechanism
			<hook x="-5.91" y="0.0" z="-0.60" length="1.416" down-angle="55" up-angle="-5">
				<control-input axis="/controls/gear/tailhook" control="HEXTEND"/>
				<control-speed control="HEXTEND" transition-time="5"/>
			</hook>-->
	<!-- Launch-bar

Note: the Seafire was not fitted with a catpult launch-bar - it used a catapult strop,
if at all. It usually did a free take-off.
the launch-bar is included here as a workable substitute.
			<launchbar x="-2.30" y="0.0" z="-1.25" length="1.0">
			 <control-input axis="/controls/gear/launchbar" control="LEXTEND"/>
				<control-speed control="LEXTEND" transition-time="1"/>
			</launchbar>-->

	<!-- Wing and Fuselage tanks.-->
	<!--Weight of contents calculated using 100 octane AVGAS density of 695 kg/m3 @ 15degC-->
	<tank x="-3.41"
				y="0.99"
				z="-0.5"
				capacity="229"/>
	<!-- left 33 imp gals -->
	<tank x="-3.41"
				y="-0.99"
				z="-0.5"
				capacity="229"/>
	<!--  right 33 imp gals -->
	<tank x="-2.56"
				y="0"
				z="0.45"
				capacity="195"/>
	<!--  centre 28 imp gals -->

	<!-- ballast and weights -->
	<!-- Cockpit, sundries-->
	<ballast x="-3.50"
					 y="0"
					 z="-0.29"
					 mass="400"/>
	<!-- armament -->
	<!-- innner guns -->
	<ballast x="-3.06"
					 y="2.27"
					 z="-0.50"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-2.27"
					 z="-0.50"
					 mass="52"/>
	<ballast x="-3.06"
					 y="2.13"
					 z="-0.51"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-2.13"
					 z="-0.51"
					 mass="52"/>
	<ballast x="-3.06"
					 y="2.00"
					 z="-0.52"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-2.00"
					 z="-0.52"
					 mass="52"/>
	<ballast x="-3.06"
					 y="1.85"
					 z="-0.53"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-1.85"
					 z="-0.53"
					 mass="52"/>
	<!-- outer guns -->
	<ballast x="-3.06"
					 y="3.46"
					 z="-0.39"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-3.46"
					 z="-0.39"
					 mass="52"/>
	<ballast x="-3.06"
					 y="3.70"
					 z="-0.43"
					 mass="52"/>
	<ballast x="-3.06"
					 y="-3.70"
					 z="-0.43"
					 mass="52"/>
	<!-- Radiator -->
	<ballast x="-3.93"
					 y="0.0"
					 z="-1.09"
					 mass="100"/>
	<!--nose ballast to fix CG-->
	<ballast x="-1.35"
					 y="0.0"
					 z="-0.45"
					 mass="90"/>
	<!-- 	 tail ballast to fix CG CG: x:-3.079, y:-0.000, z:-0.232-->
	<ballast x="-15.0"
					 y="0.0"
					 z="0.45"
					 mass="-90"/>
	<!-- pilot -->
	<weight x="-3.65"
					y="0"
					z="-0.04"
					mass-prop="/yasim/weights/pilot-lb"/>
</airplane>
