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

<fdm_config name="do228-212" 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 (D-ECHO), Kamoro </author>
		<filecreationdate> 15 Jun 2020 </filecreationdate>
		<version>06/2025</version>
		<description> Dornier DO 228-212 </description>
	</fileheader>
	
	<!--
							References:
	[1]	Pilot Operating Handbook				-
	[2]	EASA Type-Certificate Data Sheet			https://www.easa.europa.eu/sites/default/files/dfu/TCDS%20%20EASA%20A%20359%20Dornier%20228%20Issue%205.pdf
	[3]	Dornier 228 Advanced Commuter (AC) Facts & Figures	https://web.archive.org/web/20170624030020/https://ruag.picturepark.com/Go/ZeJQA0rC/V/9757/1
	[4]	TPE331-10 Turboprop Engine Brochure			https://aerospace.honeywell.com/content/dam/aero/en-us/documents/learn/products/engines/brochures/N61-1491-000-000-TPE331-10TurbopropEngine-bro.pdf?download=true
	[5]	MTV-27 EASA Type-Certificate Data Sheet			https://www.easa.europa.eu/sites/default/files/dfu/TCDS-P104-MTV-27%20series%20issue%2005.pdf
	[6]	"Love Dornier 228" (Magazine)	 			https://www.lovedornier228.com/ (no longer available)
	[7]	GoodYear Aircraft Tire Data Book			http://www.aufbau.com.ua/files/presentations/Goodyear_aircrafttire_data.pdf

	
	Airfoil: DO A-5 (https://m-selig.ae.illinois.edu/ads/aircraft.html)
	-->
	
	<!--	Some data:
			Key				Value		Reference
			MAC (Mean Aerodynamic Chord)	2.046m		[2]
	-->
	
	<!--	Location reference system:
			POH datum:	Vertical plane in front of aircraft, 7.260m in front of leading edge at MAC
			visual origin:	x=0 at leading edge of wing root, approx. 0.10m in front of leading edge at MAC
			
			so POH datum is at x=-7.160m
	-->
	
	<!--	Center of Gravity Limits (ref. [1] p.6-7	
		(at ~5180kg)
					 %MAC		x [m]
			forward:	 17.0		0.44782
			rear		 40.0		0.9184
		
		(at 6400kg)
					 %MAC		x [m]
			forward:	~27.4		0.660604
			rear 		 40.0		0.9184
	
	-->
	<metrics>
		<!--	ref. [3] unless noted otherwise	-->
		<wingarea  unit="M2">	32.00	</wingarea>
		<wingspan  unit="M" >	16.97	</wingspan>
		<wing_incidence unit="DEG"> 2.35 </wing_incidence>	<!--	guess/approximate from drawings	-->
		<chord     unit="M" >	 2.25	</chord>	<!--	guess/approximate from drawings	-->
		<htailarea unit="M2">	 8.33	</htailarea>
		<htailarm  unit="M" >	 8.9	</htailarm>	<!--	guess/approximate from drawings	-->
		<vtailarea unit="M2">	 6.0	</vtailarea>
		<vtailarm  unit="M" >	 8.5	</vtailarm>	<!--	guess/approximate from drawings	-->
		<location name="AERORP" unit="M">
			<x>	0.92	</x>	<!--	guess based on CG limits	-->
			<y>	0.00	</y>	<!--	assume symmetric design		-->
			<z>	1.04	</z>	<!--	approximate from drawings (wing center)	-->
		</location>
		<location name="EYEPOINT" unit="M">	<!--	guess/approximate from drawings	-->
			<x>	-5.0	</x>
			<y>	-0.7	</y>
			<z>	 0.5	</z>
		</location>
		<location name="VRP" unit="M">	<!--	no offset to visual model	-->
			<x>     0.0 </x>
			<y>     0.0 </y>
			<z>     0.0 </z>
		</location>
	</metrics>
	
	<mass_balance>
		<!--	y and z values are guesses or approximates from drawings unless noted otherwise	-->
		<!--	Inertia moments (ixx, iyy and izz) use values generated by YASim based on helijah's DO-228 until we have better data	-->
		<ixx unit="SLUG*FT2">  24500 </ixx>
		<iyy unit="SLUG*FT2">  86800 </iyy>
		<izz unit="SLUG*FT2"> 107000 </izz>
		<emptywt unit="KG" >	3846.9	</emptywt>	<!--	reference: correspondence with RUAG	-->
		<!--	from correspondence with RUAG: 7.898m (behind datum)	-->
		<location name="CG" unit="M">
			<x>	0.738	</x>
			<y>     0.00	</y>
			<z>	0.50	</z>
		</location>
		<!--	ref. [1] p.6-9  and following	-->
		<pointmass name="Pilot">
			<weight unit="KG"> 80.0 </weight>
			<location name="POINTMASS" unit="M">
				<x>	-2.95	</x>	<!--	-7.160m + 4.21m	-->
				<y>	-0.70	</y>
				<z>	 0.00	</z>
			</location>
		</pointmass>
		<pointmass name="Copilot">
			<weight unit="KG"> 80.0 </weight>
			<location name="POINTMASS" unit="M">
				<x>	-2.95	</x>	<!--	-7.160m + 4.21m	-->
				<y>	 0.70	</y>
				<z>	 0.00	</z>
			</location>
		</pointmass>
		<!--	For Passenger Variant	-->
		<!--	TODO this can be split up into individual seats, data for this is available in ref. [1] p.6-13	-->
		<pointmass name="PAX">
			<weight unit="KG"> 0.0 </weight>
			<location name="POINTMASS" unit="M">
				<x>	 8.61	</x>	<!--	mean value of all seats	-->
				<y>	 0.00	</y>
				<z>	 0.00	</z>
			</location>
		</pointmass>
	</mass_balance>
	
	<propulsion>
		
		<engine file="Honeywell_TPE331-10GP-511D">
			<feed> 2 </feed>
			
			<thruster file="MTV-27-1-E-C-F-R(G)">
				<sense> -1 </sense>	<!--	ref. [1] p.1-3	-->
				<location unit="M">
					<x> -0.776734 </x>
					<y> -2.53971  </y>
					<z>  0.813113 </z>
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		
		<engine file="Honeywell_TPE331-10GP-511D">
			<feed> 3 </feed>
			
			<thruster file="MTV-27-1-E-C-F-R(G)">
				<sense> -1 </sense>	<!--	ref. [1] p.1-3	-->
				<location unit="M">
					<x> -0.776734 </x>
					<y>  2.53971  </y>
					<z>  0.813113 </z>
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		
		<!--	ref. [1] p. 7-74:
			* three interconnected integral wing fuel tanks per wing
				* outboard	ca. 950 lbs = 431kg
				* inboard	ca. 880 lbs = 399kg
				* feeder	ca. 248 lbs = 113kg
					( VERY rough approximation from ref. [1] fig. 7-44 on p.7-77 )
			* total 2386l = 1885kg = 4156 lbs
			* unusable fuel: 20.5 kg drainable, 4.0kg non-drainable
				guess:	outboard: 5kg per wing (10kg overall)
					inboard: 3.5kg per wing ( 7kg overall)
					feeder:	1.75kg per wing (3.5kg overall)
		-->
		
		<!--	ref. [1] p.8-8
			Approved fuel types:
				* Jet A
				* Jet A-1
				* Jet B
				* JP-4
				* JP-5
				* JP-8
				* AVTAG
				* AVCAT
				Emergency Fuel (max. 10000ft operating altitude)
				* AVGAS
		-->
		
		<!--	ref. [1] p. 6-11: 
				* arm = 7.936m so x = -7.160 + 7.936 = 0.776m
				* density: 0.79 kg/l
			y and z values are guesses or approximates from drawings	-->
		
		<!--	Numeration:	
			0 = left outer
			1 = left inner
			2 = left feeder
			3 = right feeder
			4 = right inner
			5 = right outer	-->
		<tank type="FUEL" number="0">
			<location unit="M">
				<x>	 0.776	</x>
				<y>     -4.00	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 431 </capacity>
			<contents unit="KG"> 400 </contents>
			<unusable-volume unit="LTR"> 6.33 </unusable-volume>	<!-- 5kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
		</tank>
		<tank type="FUEL" number="1">
			<location unit="M">
				<x>	 0.776	</x>
				<y>     -2.50	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 399 </capacity>
			<contents unit="KG"> 380 </contents>
			<unusable-volume unit="LTR"> 4.43 </unusable-volume>	<!-- 3.5kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
		</tank>
		<tank type="FUEL" number="2">
			<location unit="M">
				<x>	 0.776	</x>
				<y>     -1.30	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 113 </capacity>
			<contents unit="KG"> 100 </contents>
			<unusable-volume unit="LTR"> 2.22 </unusable-volume>	<!-- 1.75kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
			<priority>1</priority>
		</tank>
		<tank type="FUEL" number="3">
			<location unit="M">
				<x>	 0.776	</x>
				<y>      1.30	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 113 </capacity>
			<contents unit="KG"> 100 </contents>
			<unusable-volume unit="LTR"> 2.22 </unusable-volume>	<!-- 1.75kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
			<priority>1</priority>
		</tank>
		<tank type="FUEL" number="4">
			<location unit="M">
				<x>	 0.776	</x>
				<y>      2.50	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 399 </capacity>
			<contents unit="KG"> 380 </contents>
			<unusable-volume unit="LTR"> 4.43 </unusable-volume>	<!-- 3.5kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
		</tank>
		<tank type="FUEL" number="5">
			<location unit="M">
				<x>	 0.776	</x>
				<y>      4.00	</y>
				<z>   	 1.04	</z>
			</location>
			<capacity unit="KG"> 431 </capacity>
			<contents unit="KG"> 400 </contents>
			<unusable-volume unit="LTR"> 6.33 </unusable-volume>	<!-- 5kg / 0.79 kg/l	-->
			<type> JET-A1 </type>
		</tank>
		
	</propulsion>
	
	<ground_reactions>
		
		<!--	all coordinates are guesses/approximations from 3d model and drawings	-->
		<contact type="BOGEY" name="NOSE">
			<location unit="M">
				<x>   -4.60  </x>
				<y>    0.00  </y>
				<z>   -1.685 </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">     8000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 4000 </damping_coeff>
			<max_steer unit="DEG"> 45.00 </max_steer>
			<brake_group> NONE </brake_group>
			<retractable> 1 </retractable>
		</contact>
		
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="M">
				<x>    1.695  </x>
				<y>   -1.703  </y>
				<z>   -1.685 </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">     20000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  6000 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> LEFT </brake_group>
			<retractable> 1 </retractable>
		</contact>
		
		<contact type="BOGEY" name="RIGHT_MAIN">
			<location unit="M">
				<x>    1.695  </x>
				<y>    1.703  </y>
				<z>   -1.685 </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">     20000 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  6000 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> RIGHT </brake_group>
			<retractable> 1 </retractable>
		</contact>
		
		<contact type="STRUCTURE" name="NOSE">
			<location unit="M">
				<x>   -4.6 </x>
				<y>    0.0 </y>
				<z>   -0.95 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      14112.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 14112.00 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="M">
				<x>   2.0  </x>
				<y>  -8.4  </y>
				<z>   1.02 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      14112.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 14112.00 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x>   2.0  </x>
				<y>   8.4  </y>
				<z>   1.02 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      14112.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 14112.00 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="TAIL">
			<location unit="M">
				<x>    7.6 </x>
				<y>    0.0 </y>
				<z>   -0.6 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      14112.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 14112.00 </damping_coeff>
		</contact>
		
	</ground_reactions>
	
	<flight_control file="Systems/do228-fcs.xml"/>
	<system file="do228-engines"/>
	<system file="do228-electrical"/>
	<system file="do228-fuel"/>
	<system file="do228-hydraulics"/>
	<system file="do228-instruments-logic"/>
	<system file="do228-rsd"/>
	<system file="do228-rain"/>
	
	<aerodynamics> <!-- see src/DO228_JSBsim_calc.ods -->
	
		<function name="aero/alpha-wing-deg">
			<todegrees>
				<property>aero/alpha-wing-rad</property>
			</todegrees>
		</function>
		
		<function name="aero/function/kCLge">
			<description>Change in lift due to ground effect</description>
			<table>
				<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
				<tableData>
					0.05	1.13
					0.1	1.09
					0.2	1.05
					0.3	1.03
					0.4	1.02
					0.6	1.01
					1.2	1.00
				</tableData>
			</table>
		</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>
							0.0     60.0
							-0.52  0.000   0.000
							0.00  0.046   0.124
							0.09  0.226   0.603
							0.18  0.000   0.000
						</tableData>
					</table>
				</product>
			</function>
			
			<!-- Lift above 0.85 and below -0.85 is generalised -->
			<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>
							-20	-1.07
							-15	-1.07
							-10	-0.57
							-5	-0.09
							5	0.82
							10	1.24
							15	1.56
							17	1.65
							20	1.56
						</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> 9.7937 </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> 3.5613 </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> 0.6982 </value>
				</product>
			</function>
			
			<function name="aero/force/Lift_flap">
				<description>Delta Lift due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar>fcs/flap-pos-deg</independentVar>
						<tableData>
							0   0.00
							5   0.19
							20   0.64
							30   0.82
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/force/Lift_aileron_droop">
				<description>Delta Lift due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<sum>
						<property>fcs/left-aileron-pos-norm</property>
						<property>fcs/right-aileron-pos-norm</property>
					</sum>
					<value> 0.0123 </value>
				</product>
			</function>
			
			
		</axis>
		
		<axis name="DRAG">
			
			<!-- CD0 is based on fuselage, wing, horizontal- en vertical tail -->
			<!-- Antennas, struts and wires are not taken into account        -->
			<!-- CD for gear (fixed and retractable) is defined below         -->
			<function name="aero/force/Drag_minimum">
				<description>Minimum drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<value> 0.0201 </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    1.4091
							-0.09    0.0295
							0.00    0.0000
							0.09    0.0295
							1.57    1.4091
						</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> 0.045 </value>
					<table>
						<independentVar lookup="row">aero/cl-squared</independentVar>
						<independentVar lookup="column">aero/h_b-mac-ft</independentVar>
						<tableData>
								0.05	0.2	0.6	1.2
							0	0.37	0.72	0.94	1.00
							1	0.46	0.74	0.94	1.00
							4	0.58	0.77	0.95	1.00
							9	0.72	0.80	0.96	1.00
							16	0.86	0.83	0.97	1.00
						</tableData>
					</table>
				</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_gear">
				<description>Drag due to gear</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>gear/gear-pos-norm</property>
					<value> 0.0300 </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>
			
			
		</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> -0.8790 </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>
							5932206   0.2978
							6525426   0.0243
							8898309   0.0108
							11847654   0.0061
						</tableData>
					</table>
				</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> 0.8805 </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> 0.2637 </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>
								0.0     60.0
							-0.01	 0.000	 0.000
							0.00	-0.03	-0.05
							0.09	-0.170	-0.3
							0.12	 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> -3.2368 </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    -3.1392
							2.0    -0.7848
						</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> -44.8541 </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> -16.3106 </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> -5.3984 </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>
					<property>fcs/gear-no-wow</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">aero/Re</independentVar>
						<tableData>
							5932206  6525426  8898309 11847654
							-0.0349  -0.0917  -0.0161  -0.0123  -0.0108
							0.3491  -0.2316  -0.0659  -0.0650  -0.0691
						</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> -1.8916 </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>
							5932206  6525426  8898309 11847654
							-0.0349  -0.0635  -0.0635  -0.0635  -0.0635
							0.3491   3.9813   1.3613   1.3613   1.3613
						</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>
					<difference>
						<property>fcs/left-aileron-pos-norm</property>
						<property>fcs/right-aileron-pos-norm</property>
					</difference>
					<value>0.8</value>
					<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> 0.2116 </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>
							5932206  -0.1492
							6525426  -0.0122
							8898309  -0.0054
							11847654  -0.0031
						</tableData>
					</table>
				</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> -0.2241 </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> -0.1321 </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>
					<difference>
						<property>fcs/left-aileron-pos-norm</property>
						<property>fcs/right-aileron-pos-norm</property>
					</difference>
					<value> -0.0100 </value>
				</product>
			</function>
			
		</axis>
		
	</aerodynamics>
	
	<external_reactions>
	</external_reactions>
	
</fdm_config>
