<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>

<fdm_config name="BN-2" version="2.0" release="ALPHA"
		xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
		xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
	
	<fileheader>
		<author>Bea Wolf using Aeromatic v 3.3.10</author>
		<filecreationdate> 08 Jun 2022 </filecreationdate>
		<version>11/2023</version>
		<description> Models a BN-2A-26 </description>
	</fileheader>
	
	<!--
	References:
	FM	Approved Flight Manual FM/7				https://www.scribd.com/document/254126653/BN-2-Flight-Manual-pdf
	EOM	Lycoming O-540, IO-540 Series Operator's Manual		https://www.lycoming.com/sites/default/files/O%20%26%20IO-540%20Oper%20Manual%2060297-10.pdf
	TCDS_A	BN-2 Type Certificate Data Sheet			https://www.easa.europa.eu/downloads/7148/en
	TCDS_E	Lycoming O540 Type Certificate Data Sheet		https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/93856fc09b9f3b5686257b63006c422f/$FILE/E-295_Rev_19.pdf
	-->
	
	<!--	Flight Manual (FM) CG Reference Datum (ref. FM, Section 6, Page 2f.) :	
	
	Name			Station			Wing Leading Edge = CG Datum
	Station			0			-134.5 in = -3.4163 m	
	Nose			3.75 in = 0.09525 m	-130.75 in = -3.3211 m	
	Wing Leading Edge	134.5 in = 3.4163 m	0			
	= CG Datum
	-->
	
	<metrics>
		<!--	Ref. FM, Section 1, Page 4	-->
		<wingarea  unit="M2"> 30.20 </wingarea>
		<wingspan  unit="M" > 14.92 </wingspan>
		<wing_incidence unit="DEG"> 2.00 </wing_incidence>
		<chord     unit="M" >  2.04 </chord>
		<htailarea unit="M2">  6.61 </htailarea>
		<htailarm  unit="M" >  5.0 </htailarm> <!-- assumption from drawing -->
		<vtailarea  unit="M2"> 3.22 </vtailarea>
		<vtailarm  unit="M" >  5.0 </vtailarm> <!-- assumption from drawing -->
		<location name="AERORP" unit="M"> <!-- assume: 25% root wing chord: 0.51 m aft of wing leading edge -->
			<x> 0.51  </x>
			<y> 0.00  </y>
			<z> 0.00  </z> <!-- TODO -->
		</location>
		<location name="EYEPOINT" unit="IN"> <!-- TODO -->
			<x>    72.95 </x>
			<y>   -18.00 </y>
			<z>    45.00 </z>
		</location>
		<location name="VRP" unit="IN">
			<x>     0.0 </x>
			<y>     0.0 </y>
			<z>     0.0 </z>
		</location>
	</metrics>
	
	<mass_balance>
		<ixx unit="SLUG*FT2">   5322.90 </ixx>
		<iyy unit="SLUG*FT2">   4773.88 </iyy>
		<izz unit="SLUG*FT2">  11070.32 </izz>
		<emptywt unit="KG"  >   1860.0  </emptywt> <!-- Ref. FM, Section 6, Page 5: 4100 lb ~ 1860 kg; - 80 kg (pilot) = 1780 kg -->
		<location name="CG" unit="M">
			<!-- Empty CG, ref. FM, Section 6, Page 5: 90 600 lb*in / 4100 lb = 22.098 in = 0.5613 m (CG datum) -->
			<x> 0.5613 </x>
			<y> 0.0    </y>
			<z> 0.0    </z> <!-- TODO -->
		</location>
		<!--	Seat Rows (ref. FM, Section 6, Page 10):
		Station [in]	CG Datum [in]	[m]		FG Designation
		Seat Row 1 (Pilot/Copilot)	89		-45.5		-1.1557		Pilot/Copilot
		Seat Row 2			120		-14.5		-0.3683		Seat 1L and 1R
		Seat Row 3			150		+15.5		+0.3937		Seat 2L and 2R
		Seat Row 4			179		+44.5		+1.1303		Seat 3L and 3R
		Seat Row 5			207		+72.5		+1.8415		Seat 4L and 4R
		-->
		<pointmass name="Pilot">
			<weight unit="KG"> 80 </weight>
			<location name="POINTMASS" unit="M">
				<x> -1.1557 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Copilot">
			<weight unit="KG"> 80 </weight>
			<location name="POINTMASS" unit="M">
				<x> -1.1557 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 1L">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x> -0.3683 </x>
				<y> -0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 1R">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x> -0.3683 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 2L">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  0.3937 </x>
				<y> -0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 2R">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  0.3937 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 3L">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  1.1303 </x>
				<y> -0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 3R">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  1.1303 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 4L">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  1.8415 </x>
				<y> -0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Seat 4R">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  1.8415 </x>
				<y>  0.27 </y> <!-- estimate -->
				<z>  0 </z> <!-- TODO -->
			</location>
		</pointmass>
		<!-- Cargo/Baggage (ref. FM, Section 6, Page 8):
		
		Station [in]	CG Datum [in]	[m]		FG Designation
		Fwd of Front Spar		122		-12.5		-0.3175		Cargo Front
		Between Spars			162		+27.5		+0.6985		Cargo Center
		Aft of Rear Spar		194		+59.5		+1.5113		Cargo Rear
		Station 240			240		+105.5		+2.6797		Baggage Front
		S				Station 255.5			255.5		+121		+3.0734		Baggage Rear (Extension)
		-->
		<pointmass name="Cargo Front">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x> -0.3175 </x>
				<y>  0.0 </y>
				<z>  0   </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Cargo Center">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  0.6985 </x>
				<y>  0.0 </y>
				<z>  0   </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Cargo Rear">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  1.5113 </x>
				<y>  0.0 </y>
				<z>  0   </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Baggage Front">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  2.6797 </x>
				<y>  0.0 </y>
				<z>  0   </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Baggage Rear (Extension)">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<x>  3.0734 </x>
				<y>  0.0 </y>
				<z>  0   </z> <!-- TODO -->
			</location>
		</pointmass>
		<pointmass name="Ice">
			<weight unit="KG"> 0 </weight>
			<location name="POINTMASS" unit="M">
				<!-- Empty CG, ref. FM, Section 6, Page 5: 90 600 lb*in / 4100 lb = 22.098 in = 0.5613 m (CG datum) -->
				<x> 0.5613 </x>
				<y> 0.0    </y>
				<z> 0.0    </z> <!-- TODO -->
			</location>
		</pointmass>
	</mass_balance>
	
	<propulsion>
		
		<!-- ref. FM, p. 122 -->
		<!-- Engine CG: -2.0 in = -0.0508 m -->
		<!-- Propeller CG: -24.0 in = -0.6096 m -->
		
		<engine file="Lycoming_O-540-E4C5">
			<feed> 2 </feed>
			
			<thruster file="HC-C2YK-2B_8477-4">
				<sense> 1 </sense>
				<location unit="M">
					<x> -0.6096 </x>
					<y> -1.8 </y> <!-- approx. from 3d model -->
					<z>  0 </z> <!-- TODO -->
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		
		<engine file="Lycoming_O-540-E4C5">
			<feed> 3 </feed>
			
			<thruster file="HC-C2YK-2B_8477-4">
				<sense> 1 </sense>
				<location unit="M">
					<x> -0.6096 </x>
					<y>  1.8 </y> <!-- approx. from 3d model -->
					<z>  0 </z> <!-- TODO -->
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		<!-- ref. FM, p. 118 -->
		<tank type="FUEL" number="0">
			<location unit="M">
				<x> 0.6858 </x> <!-- +27.0 in = +0.6858 m -->
				<y> 0 </y> <!-- TODO -->
				<z> 0 </z> <!-- TODO -->
			</location>
			<!-- ref. FM, Section 2, Page 4 -->
			<capacity unit="LBS"> 412.37 </capacity> <!-- 65.0 US gal usable + 3.5 US gal unusable -->
			<contents unit="LBS"> 200    </contents>
			<unusable unit="GAL">   3.5  </unusable>
			<type>AVGAS</type> <!-- 6.02 lbs/US Gal -->
		</tank>
		<tank type="FUEL" number="1">
			<location unit="M">
				<x> 0.6858 </x> <!-- +27.0 in = +0.6858 m -->
				<y> 0 </y> <!-- TODO -->
				<z> 0 </z> <!-- TODO -->
			</location>
			<!-- ref. FM, Section 2, Page 4 -->
			<capacity unit="LBS"> 412.37 </capacity> <!-- 65.0 US gal usable + 3.5 US gal unusable -->
			<contents unit="LBS"> 200    </contents>
			<unusable unit="GAL">   3.5  </unusable>
			<type>AVGAS</type> <!-- 6.02 lbs/US Gal -->
		</tank>
		<!--	Carburetor "Tanks"	-->
		<tank type="FUEL" number="2">
			<location unit="M">
				<x> -0.0254 </x> <!-- ref. FM, p.112 -->
				<y> -1.8 </y> <!-- approx. from 3d model -->
				<z>  0  </z> <!-- TODO -->
			</location>
			<capacity unit="LBS"> 0.01 </capacity>
			<contents unit="LBS"> 0.0  </contents>
			<type>AVGAS</type> <!-- 6.02 lbs/US Gal -->
		</tank>
		<tank type="FUEL" number="3">
			<location unit="M">
				<x> -0.0254 </x> <!-- ref. FM, p.112 -->
				<y>  1.8 </y> <!-- approx. from 3d model -->
				<z>  0  </z> <!-- TODO -->
			</location>
			<capacity unit="LBS"> 0.01 </capacity>
			<contents unit="LBS"> 0.0  </contents>
			<type>AVGAS</type> <!-- 6.02 lbs/US Gal -->
		</tank>
		
	</propulsion>
	
	<ground_reactions>
		<contact type="BOGEY" name="NOSE">
			<location unit="M">
				<x> -2.9591 </x>
				<y>  0.0    </y>
				<z> -1.7    </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff  unit="LBS/FT">     2000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 945.28 </damping_coeff>
			<max_steer unit="DEG"> 30.00 </max_steer>
			<brake_group> NONE </brake_group>
			<retractable> 0 </retractable>
		</contact>
		
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="M">
				<x>  1.034 </x>
				<y> -1.805 </y>
				<z> -1.68  </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff  unit="LBS/FT">     7000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 3150.94 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> LEFT </brake_group>
			<retractable> 0 </retractable>
		</contact>
		
		<contact type="BOGEY" name="RIGHT_MAIN">
			<location unit="M">
				<x>  1.034 </x>
				<y>  1.805 </y>
				<z> -1.68  </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff  unit="LBS/FT">     7000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 3150.94 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> RIGHT </brake_group>
			<retractable> 0 </retractable>
		</contact>
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="M">
				<x>  1.0  </x>
				<y> -6.85 </y>
				<z>  0.15 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      6301.89 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 6301.89 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x>  1.0  </x>
				<y>  6.85 </y>
				<z>  0.15 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      6301.89 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 6301.89 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="TAIL_LOW">
			<location unit="M">
				<x>  6.8  </x>
				<y>  0.0  </y>
				<z> -0.33 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      6301.89 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 6301.89 </damping_coeff>
		</contact>
		
	</ground_reactions>
	
	<flight_control file="Systems/bn2-fcs.xml" />
	
	<system file="fuel" />
	<system file="instruments" />
	
	<aerodynamics>
		
		<function name="aero/alpha-wing-deg">
			<todegrees>
				<property>aero/alpha-wing-rad</property>
			</todegrees>
		</function>
		
		<axis name="LIFT">
			
			<function name="aero/force/Lift_propwash">
				<description>Delta lift due to propeller induced velocity</description>
				<product>
					<property>systems/propulsion/thrust-coefficient</property>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
						<tableData><!-- temporarily from QSeries aerodynamics, by Joshua Davidson -->
							0	60
							-0.10	0.000	0.000
							0.00	0.020	0.043
							0.19	0.105	0.231
							0.39	0.000	0.000
						</tableData>
					</table>
				</product>
			</function>
			
			<!-- Lift above 0.85 and below -0.85 is generalised -->
			
			<!--	Calculate Cl, max from V,s0:
			
			ref. FM, Section 4, Pag 19:
			
			all data at 6300 lbs = 2858 kg
			
			IAS to CAS calibration see ref. FM, Section 5, Page 9, curve for 6600 lbs used
			
			Flap		Stall (IAS)			Stall (CAS)		Cl required (see below)		factor (table Cl,max = 1.8467)
			0 deg		50 kts = 25.72 mps	57 kts = 29.32 mps	1.763				0.9547
			25 deg	45 kts = 23.15 mps	51 kts = 26.24 mps	2.201				1.1919
			56 deg	43 kts = 22.12 mps	47 kts = 24.18 mps	2.592				1.4036
			
			gravitational force: Fg = m * g = 2858 kg * 9.81 N/kg = 28 037 N
			
			lift force: Fl = 0,5 * rho * v^2 * A * Cl
			
			assume: rho = 1.225 kg/m3
			
			A = 30.20 m2 (ref. FM, Section 1, Page 4)
			
			Fl = Fg
			0,5 * 1,225 kg/m3 * v^2 * 30.20 m2 * Cl = 28 037 N
			Cl = 1515.72 Nm/kg / v^2
			-->
			<function name="aero/force/Lift_alpha">
				<description>Lift due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-wing-deg</independentVar>
						<tableData>
							-90	0
							-15	-1.5248
							-12.5	-1.2908
							-10	-1.0071
							-7.5	-0.7315
							-5	-0.4448
							-2.5	-0.1537
							0	0.1383
							2.5	0.4233
							5	0.7157
							7.5	0.999
							10	1.2988
							12.5	1.5403
							15	1.7528
							17.5	1.8467
							20	1.6951
							22.5	1.3644
							25	1.2991
							27.5	1.2732
							30	1.2803
							32.5	1.2982
							35	1.3217
							40	0.7606
							90	0
						</tableData>
					</table>
					<table>
						<independentVar>fcs/flap-pos-deg</independentVar>
						<tableData>
							0	0.9457
							25	1.1919
							56	1.4036
						</tableData>
					</table>
					<!-- adapted from SenecaII by Torsten Dreyer-->
					<table>
						<independentVar>ice/wing</independentVar>
						<tableData>
							0.0	1.0
							0.5	0.875
							1.0	0.75
							2.0	0.5
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/force/Lift_pitch_rate">
				<description>Lift due to pitch rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>velocities/q-aero-rad_sec</property>
					<property>aero/ci2vel</property>
					<value> 4.3811 </value>
				</product>
			</function>
			
			<function name="aero/force/Lift_alpha_rate">
				<description>Lift due to alpha rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/alphadot-rad_sec</property>
					<property>aero/ci2vel</property>
					<value> 1.8643 </value>
				</product>
			</function>
			
			<function name="aero/force/Lift_elevator">
				<description>Lift due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/elevator-pos-rad</property>
					<value> 0.5870 </value>
				</product>
			</function>
			
			
		</axis>
		
		<axis name="DRAG">
			
			<function name="aero/force/Drag_minimum">
				<description>Minimum drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<value> 0.0206 </value>
				</product>
			</function>
			
			<function name="aero/force/Drag_alpha">
				<description>Drag due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-1.57    1.4089
							-0.34    0.0770
							0.00    0.0000
							0.34    0.0770
							1.57    1.4089
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/force/Drag_induced">
				<description>Induced drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/cl-squared</property>
					<value> 0.0451 </value>
				</product>
			</function>
			
			<function name="aero/force/Drag_mach">
				<description>Drag due to mach</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
							0.00    0.0000
							0.72    0.0000
							1.10    0.0230
							1.80    0.0150
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/force/Drag_beta">
				<description>Drag due to sideslip</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/beta-rad</independentVar>
						<tableData>
							-1.57    1.2300
							-0.26    0.0500
							0.00    0.0000
							0.26    0.0500
							1.57    1.2300
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/force/Drag_elevator">
				<description>Drag due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<abs><property>fcs/elevator-pos-rad</property></abs>
					<value> 0.0400 </value>
				</product>
			</function>
			
			<function name="aero/force/Drag_flap">
				<description>Drag due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/flap-pos-deg</property>
					<value> 0.0012 </value>
				</product>
			</function>
			
			<!--taken from SenecaII by Torsten Dreyer-->
			<function name="aero/force/Drag_ice_wing">
				<description>Drag_due_to_ice_on_wing</description>
				<product>
					<property>aero/qbar-area</property>
					<table>
						<independentVar>ice/wing</independentVar>
						<tableData>
							0.0      0
							0.5      0.09
							1.0      0.15
							2.0      0.5
						</tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Drag_ice_fuselage">
				<description>Drag_due_to_ice_on_fuselage</description>
				<product>
					<property>aero/qbar-area</property>
					<table>
						<independentVar>ice/fuselage</independentVar>
						<tableData>
							0.0      0
							0.5      0.05
							1.0      0.1
							2.0      0.25
						</tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Drag_ice_stabilizer">
				<description>Drag_due_to_ice_on_stabilizer</description>
				<product>
					<property>aero/qbar-area</property>
					<table>
						<independentVar>ice/stabilizer</independentVar>
						<tableData>
							0.0      0
							0.5      0.015
							1.0      0.05
							2.0      0.125
						</tableData>
					</table>
				</product>
			</function>
			
		</axis>
		
		<axis name="SIDE">
			
			<function name="aero/force/Side_beta">
				<description>Side force due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/beta-rad</property>
					<value> -0.4969 </value>
				</product>
			</function>
			<function name="aero/force/Side_roll_rate">
				<description>Side force due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-aero-rad_sec</property><!--
					<table>
					<independentVar lookup="row">aero/Re</independentVar>
					<tableData>
					3599238   0.4242
					3959163   0.0347
					5398858   0.0154
					7198654   0.0087
					</tableData>
					</table>-->
					<value>0.0087</value>
				</product>
			</function>
			
			<function name="aero/force/Side_yaw_rate">
				<description>Side force due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<value> 0.3331 </value>
				</product>
			</function>
			
			<function name="aero/force/Side_rudder">
				<description>Side force due to rudder</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> 0.1500 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="PITCH">
			
			<function name="aero/moment/Pitch_propwash">
				<description>Pitch moment due to propeller induced velocity</description>
				<product>
					<property>systems/propulsion/thrust-coefficient</property>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
						<tableData> <!-- temporarily adapted from Q400 Aerodynamics by Joshua Davidson -->
							0      60
							-0.01  0.000  0.000
							0.00 -0.000 -0.001
							0.19 -0.002 -0.005
							0.25  0.000  0.000
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/moment/Pitch_alpha">
				<description>Pitch moment due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/alpha-rad</property>
					<value> -0.8 </value>
				</product>
			</function>
			
			<function name="aero/moment/Pitch_elevator">
				<description>Pitch moment due to elevator</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>fcs/elevator-pos-rad</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
							0.0    -1.3939
							2.0    -0.3485
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/moment/Pitch_damp">
				<description>Pitch moment due to pitch rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>velocities/q-aero-rad_sec</property>
					<value> -10.7380 </value>
				</product>
			</function>
			
			<function name="aero/moment/Pitch_alphadot">
				<description>Pitch moment due to alpha rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>aero/alphadot-rad_sec</property>
					<value> -4.5693 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="ROLL">
			
			<!--<function name="aero/moment/Roll_differential_propwash">
			<description>Roll moment due to differential propwash</description>
			<product>
			<property>systems/propulsion/thrust-coefficient-left-right</property>
			<property>aero/qbar-psf</property>
			<property>metrics/Sw-sqft</property>
			<property>metrics/bw-ft</property>
			<property>aero/alpha-rad</property>
			<value> -3115.0959 </value>
			</product>
			</function>-->
			
			<function name="aero/moment/Roll_beta">
				<description>Roll moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property><!--
					<table>
					<independentVar lookup="row">aero/alpha-rad</independentVar>
					<independentVar lookup="column">aero/Re</independentVar>
					<tableData>
					3599238  3959163  5398858  7198654
					-0.0349  -0.3798  -0.0378  -0.0209  -0.0150
					0.3491  -0.3798  -0.0378  -0.0209  -0.0150
					</tableData>
					</table>-->
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-0.0349 -0.0150
							0.3491  -0.0150
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/moment/Roll_damp">
				<description>Roll moment due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-aero-rad_sec</property>
					<value> -0.6055 </value>
				</product>
			</function>
			
			<function name="aero/moment/Roll_yaw">
				<description>Roll moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property><!--
					<table>
					<independentVar lookup="row">aero/alpha-rad</independentVar>
					<independentVar lookup="column">aero/Re</independentVar>
					<tableData>
					3599238  3959163  5398858  7198654
					-0.0349   0.0635   0.0635   0.0635   0.0635
					0.3491   5.7194   0.5766   0.5766   0.5766
					</tableData>
					</table>-->
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-0.0349   0.0635
							0.3491   0.5766
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/moment/Roll_aileron">
				<description>Roll moment due to aileron</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-aileron-pos-rad</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
							0.0    0.1700
							2.0    0.0425
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/moment/Roll_rudder">
				<description>Roll moment due to rudder</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> 0.0100 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="YAW">
			
			
			<function name="aero/moment/Yaw_beta">
				<description>Yaw moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property>
					<value> 0.0800 </value>
				</product>
			</function>
			
			<function name="aero/moment/Yaw_roll_rate">
				<description>Yaw moment due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-rad_sec</property><!--
					<table>
					<independentVar lookup="row">aero/Re</independentVar>
					<tableData>
					3599238  -0.1421
					3959163  -0.0116
					5398858  -0.0052
					7198654  -0.0029
					</tableData>
					</table>-->
					<value>-0.0029</value>
				</product>
			</function>
			
			<function name="aero/moment/Yaw_damp">
				<description>Yaw moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<value> -0.0758 </value>
				</product>
			</function>
			
			<function name="aero/moment/Yaw_rudder">
				<description>Yaw moment due to rudder</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> -0.0503 </value>
				</product>
			</function>
			
			<function name="aero/moment/Yaw_aileron">
				<description>Adverse yaw</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-aileron-pos-rad</property>
					<value> -0.0100 </value>
				</product>
			</function>
			
		</axis>
		
	</aerodynamics>
	
	<external_reactions>
	</external_reactions>
	
</fdm_config>
