<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Dragonfly" version="2.0" release="ALPHA"
	    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
	    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
	
	<!-- References:
	[1]	Pilot Operating Handbook (Rev. 5)	http://pitmanair.com/dragonfly/manuals/POHRev5.pdf
	[2]	Maintenance Manual	http://pitmanair.com/dragonfly/manuals/MM_DF_912_Rev3_2017red.pdf
	[3]	Geraetekennblatt  	https://www.daec.de/fileadmin/user_upload/files/2012/luftsportgeraete_buero/kennblaetter/191.pdf
	[4]	Lifting-Line Predictions for Induced Drag and Lift in Ground Effect, Phillips and Hunsaker,
	   	https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=1086&context=mae_facpub -->
	<!--
	From the POH
	http://www.moyesamerica.com/forms/DragonflyFlightManual.pdf
	
	Datum is at nose
	
	**** Dimensions ****
	Leading Edge is at 1524mm
	Empty weight is 248 kg
	Max Weight is 450kg
	Datum is at nose
	MAC is 1638mm
	
	**** Speeds ****
	Vne at 450kg 56mph
	Vne at 300kg 66mph
	Vs at 450kg 28mph
	Vs at 300kg 20mph
	
	**** CG ****
	max forward 1921mm or 24.2% MAC
	max aft 2077 or 33.8% MAC
	Empty Weight CG is at 2407mm or 53.9% MAC
	Pilot arm (front seat) is 889mm
	Copilot arm (aft seat) is 2082mm
	Fuel arm is 1524mm
	
	**** Performance ****
	with Rotax 582 and 6 blade ivo prop on 4:1 gearbox
	5000RPM gives 45mph
	
	best ROC (Vy)
	TOW 340kg 1100ft/min@32mph
	TOW 430kg  700ft/min@45mph
	
	best glide
	TOW 340kg 450ft/min@35mph  7 to one    Ca=1.135 Cw=0.164 (old)  Ca=1.292 Cw=0.191 (new)
	TOW 430kg 550ft/min@45mph  7.5 to one  Ca=1.135 Cw=0.158 (old)  Ca=0.991 Cw=0.132 (new)
	
	minimum sink rate
	TOW 340kg 450ft/min@35mph       Ca=1.135 Cw=0.164 (old)  Ca=1.292 Cw=0.191 (new)
	TOW 430kg 550ft/min@35mph       Ca=1.436 Cw=0.256 (old)  Ca=1.626 Cw=0.294 (new)
	
	**** Axis orientation ****
	X points back
	Y points right
	Z points up
	-->
	
	<!-- 
	  Important: 
	     - Wing pitch angle is +13.0deg
	     - Horizontal stabilizer pitch angle is 0.0deg
	     - Wing twist is -2.0deg
	     Here flow angle is according to Horizontal Stabilizer.
	     Hence alpha=0.0deg is alpha +13.0deg for wing
	
	     All locations in JSBSim according to Dragonfly.ac model
	     JSBSim_location = FlightManual_location - 2,285m  (2,285m is difference of Front Wheel Axle)
	-->
	
	<fileheader>
		<author>Torsten Dreyer, Bea Wolf, D-NXKT</author>
		<filecreationdate>2006-12-30</filecreationdate>
		<version>0.5</version>
		<description>Models a Moyes Dragonfly ultralight aircraft</description>
	</fileheader>
	
	<metrics>
		<wingarea unit="M2">17.02</wingarea>
		<wingspan unit="M">10.39</wingspan>
		<wing_incidence unit="DEG">13.0</wing_incidence>
		<chord unit="M">1.638</chord>
		<!--
		<htailarea unit="M2">1.479</htailarea>
		<htailarm unit="M">3.656</htailarm>
		<vtailarea unit="M2">1.70</vtailarea>
		<vtailarm unit="M">3.656</vtailarm>
		-->
		<!-- 
		the aerodynamic reference point, common point for 
		aerodynamic forces (lift and drag) 
		Assume at average of max CG forward and aft or 29% MAC
		-->
		
		<location name="AERORP" unit="M">
			<x> -0.337973</x>
			<y> 0.00 </y>
			<z> 1.07572 </z>
		</location>
		<location name="EYEPOINT" unit="M">
			<x>-1.03321</x>
			<y>0.00</y>
			<z>0.607908</z>
		</location>
		<location name="VRP" unit="M">
			<x>0</x>
			<y>0</y>
			<z>0</z>
		</location>
	</metrics>
	
	<!--	Mass and Balance:
	see 	[1]	pages 19-21
	[2]	pages 14-16
	[3]	page 2
	-->
	<mass_balance>
		<ixx unit="SLUG*FT2"> 395</ixx>
		<iyy unit="SLUG*FT2"> 200</iyy>
		<izz unit="SLUG*FT2">562</izz>
		<ixy unit="SLUG*FT2">0</ixy>
		<ixz unit="SLUG*FT2">0</ixz>
		<iyz unit="SLUG*FT2">0</iyz>
		
		<emptywt unit="KG">225</emptywt>
		
		<location name="CG" unit="M">
			<x> 0.122 </x>
			<y> 0.00  </y>
			<z> 0.35 </z>
		</location>
		
		<pointmass name="PILOT">
			<weight unit="KG">90.0</weight>
			<location name="POINTMASS" unit="M">
				<x> -1.396 </x>
				<y>  0.0   </y>
				<z> -0.06  </z>
			</location>
		</pointmass>
		
		<pointmass name="CO-PILOT">
			<weight unit="KG">0.0</weight>
			<location name="POINTMASS" unit="M">
				<x> -0.203 </x>
				<y>  0.0   </y>
				<z>  0.06  </z>
			</location>
		</pointmass>
		
		<pointmass name="Instruments">
			<weight unit="KG">0.0</weight>
			<location name="POINTMASS" unit="M">
				<x> -1.835 </x>
				<y>  0.262 </y>
				<z>  0.020 </z>
			</location>
		</pointmass>
		
		<pointmass name="Floats">
			<weight unit="KG">0.0</weight>
			<location name="POINTMASS" unit="M">  <!-- prepared for the future -->
				<x>  0.0 </x>
				<y>  0.0 </y>
				<z>  0.0 </z>
			</location>
		</pointmass>
		
	</mass_balance>
	
	<ground_reactions>
		
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="M">
				<x> -1.01499 </x>
				<y> -0.933645 </y>
				<z> -0.744696 </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">        1200.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">   200.00 </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> -1.01499 </x>
				<y>  0.933645 </y>
				<z> -0.744696 </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">        1200.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">   200.00 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group>RIGHT</brake_group>
			<retractable>0</retractable>
		</contact>
		
		<contact type="BOGEY" name="TAIL">
			<location unit="M">
				<x>  2.642 </x>
				<y>  0.00   </y>
				<z> -0.71972 </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">1400.00</spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">300.00</damping_coeff>
			<max_steer unit="DEG">-15.00</max_steer>
			<brake_group>NONE</brake_group>
			<retractable>0</retractable>
		</contact>
		
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="M">
				<x>-0.152567</x>
				<y>-4.97715</y>
				<z> 1.24719</z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">       1000.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">   200.00 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x>-0.152567</x>
				<y> 4.97715</y>
				<z> 1.24719</z>
			</location>
			<static_friction>0.80</static_friction>
			<dynamic_friction>0.50</dynamic_friction>
			<spring_coeff unit="LBS/FT">1000.00</spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">200.00</damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="NOSE">
			<location unit="IN">
				<x>-2.29262</x>
				<y>0</y>
				<z>-0.136512</z>
			</location>
			<static_friction>0.80</static_friction>
			<dynamic_friction>0.50</dynamic_friction>
			<spring_coeff unit="LBS/FT">1000.00</spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">200.00</damping_coeff>
		</contact>
		
	</ground_reactions>
	
	<propulsion>
		
		<engine file="Rotax582">
			<feed>0</feed>
			
			<thruster file="Neuform.tr3-73-25,4-100">
				
				<location unit="M">
					<x>0.86</x>
					<y>0.00</y>
					<z>0.95</z>
				</location>
				
				<orient unit="DEG">
					<pitch> 0.00 </pitch>
					<roll>   0.00 </roll>
					<yaw>   0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		
		<tank type="FUEL" number="0">
			
			<location unit="M">
				<x> -0.743 </x>
				<y>  0.00  </y>
				<z>  0.09  </z>
			</location>
			
			<capacity unit="KG">15.0</capacity>
			<contents unit="KG">10.0</contents>
		</tank>
		
	</propulsion>
	
	
	<flight_control file="Systems/dragonfly-fcs"/>
	
	<aerodynamics>
		
		<description>
			Ground effect: Influence on lift
			Ref. Hoerner and Borst, Fluid-Dynamic Lift, 20-10
			Quotation "Theory predicts that roughly below CL = 1.5 lift will be increased in 
			proximity of the ground, while above that coefficient with wing flaps deflected, 
			for example, there will be a REDUCTION of the sectional lift"
			Dragonfly: CL_max = 2.5 with (steady) flaps.
			Hence influence of ground effect on lift is omitted (to be on the safe side).
		</description>
		
		<function name="aero/k_GroundEffect_cd">   <!-- Ref. 4 p 2 eq. 4 -->
			<description>Factor for drag reduction due to ground effect</description>
			<difference>
				<value>1.</value>
				<exp>
					<product>
						<value>-2.48</value>
						<pow>
							<product>
								<value>0.06</value>
								<!-- aero/h_b-mac-ft is completly wrong (Bug JSBSim Status May 2020) -->
								<sum>
									<property>position/h-agl-ft</property>
									<value>2.38</value>
								</sum>
							</product>
							<value>0.768</value>
						</pow>
					</product>
				</exp>
			</difference>
		</function>
		
		<function name="aero/qbarUUprop-psf">
			<description>dynamic pressure for empennage (takes propeller induced velocity into account)</description>
			<product>
				<value>0.5</value>
				<property>atmosphere/rho-slugs_ft3</property>
				<pow>
					<sum>
						<property>velocities/u-aero-fps</property>
						<property>propulsion/engine[0]/prop-induced-velocity_fps</property>
					</sum>
					<value>2</value>
				</pow>
			</product>
		</function>
		
		<function name="aero/qbarU-psf">
			<description>dynamic pressure for Clda (aileron efficiency is alpha dependent)</description>
			<product>
				<value>0.5</value>
				<property>atmosphere/rho-slugs_ft3</property>
				<pow>
					<property>velocities/u-aero-fps</property>
					<value>2</value>
				</pow>
			</product>
		</function>
		
		<axis name="LIFT">
			
			<function name="aero/coefficient/CLalpha">
				<description>Lift_due_to_alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							-180   	 0.8000
							-165   	 0.8000
							-150   	 0.8000
							-135   	 0.6500
							-120   	 0.4500
							-105.00	 0.0000
							 -90   	-0.5500
							 -75   	-0.9000
							 -60   	-0.9500
							 -45   	-0.9700
							 -42.5 	-1.0000
							 -40   	-1.1000
							 -37.5 	-1.1800
							 -35   	-1.2000
							 -32.5 	-1.2000
							 -30   	-1.1166
							 -27.5 	-0.9305
							 -25   	-0.7444
							 -22.5 	-0.5583
							 -20   	-0.3722
							 -17.5 	-0.1861
							 -15.00	 0.0000
							 -12.5 	 0.1861
							 -10   	 0.3722
							  -7.5 	 0.5583
							  -5   	 0.7444
							  -2.5 	 0.9305
							  -1.69	 0.9908
							   0   	 1.1166
							   2.36	 1.2923
							   6.84	 1.6257
							  10   	 1.8610
							  12.5 	 2.0471
							  15   	 2.2332
							  18.58	 2.5000
							  20   	 2.4800
							  22.5 	 2.4000
							  25   	 2.2000
							  27.5 	 2.0000
							  30   	 1.9600
							  32.5 	 1.9000
							  35   	 1.8500
							  37.5 	 1.8000
							  40   	 1.7000
							  42.5 	 1.6000
							  45   	 1.5000
							  60   	 0.7500
							  75.00	 0.0000
							  90   	-0.4500
							 105   	-0.6500
							 120   	-0.8000
							 135   	-0.8000
							 150   	-0.8000
							 165.00	 0.0000
							 180   	 0.8000
						</tableData>
					</table>
				</product>
			</function>
		<!--
			<function name="aero/coefficient/CLde">
			<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>0.2</value>
			</product>
			</function>
		-->
		</axis>
		
		<axis name="DRAG">
			
			<function name="aero/coefficient/CDalpha">
				<description>Drag_due_to_alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							-180   	0.0772
							-165   	0.7457
							-150   	0.9157
							-135   	1.0774
							-120   	1.1691
							-105.00	1.2000
							 -90   	1.1638
							 -75   	1.0966
							 -60   	1.0016
							 -45   	0.8296
							 -42.5 	0.7964
							 -40   	0.7551
							 -37.5 	0.7054
							 -35   	0.6528
							 -32.5 	0.6039
							 -30   	0.5619
							 -27.5 	0.4744
							 -25   	0.3956
							 -22.5 	0.3255
							 -20   	0.2640
							 -17.5 	0.2113
							 -15.00	0.1673
							 -12.5 	0.1320
							 -10   	0.1054
							  -7.5 	0.0875
							  -5   	0.0783
							  -2.5 	0.0778
							  -1.69	0.0795
							   0   	0.0860
							   2.36	0.1016
							   6.84	0.1529
							  10   	0.2058
							  12.5 	0.2574
							  15   	0.3178
							  18.58	0.4196
							  20   	0.4603
							  22.5 	0.5213
							  25   	0.6206
							  27.5 	0.7056
							  30   	0.7541
							  32.5 	0.7965
							  35   	0.8466
							  37.5 	0.8763
							  40   	0.9151
							  42.5 	0.9528
							  45   	0.9894
							  60   	1.1499
							  75.00	1.2000
							  90   	1.1691
							 105   	1.0774
							 120   	0.9157
							 135   	0.7457
							 150   	0.4182
							 165.00	0.1673
							 180   	0.0772
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/coefficient/CDi">
				<description>Induced_drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/cl-squared</property>
					<value>0.0536</value>
					<property>aero/k_GroundEffect_cd</property>
				</product>
			</function>
			
			<function name="aero/coefficient/CDbeta">
				<description>Drag_due_to_sideslip (not yet checked)</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/beta-rad</independentVar>
						<tableData>
							-1.57       1.230
							-0.26    0.050
							0.00       0.000
							0.26    0.050
							1.57       1.230
						</tableData>
					</table>
				</product>
			</function>
			
		<!--
			<function name="aero/coefficient/CDde">
				<description>Drag_due_to_Elevator_Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<abs><property>fcs/elevator-pos-norm</property></abs>
					<value>0.05</value>
				</product>
			</function>
		-->
			<function name="aero/coefficient/CDbanner">
				<description>Drag_due_to_banner</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/speedbrake-pos-norm</property>
					<value>0.01</value>
<value>0.0</value>
				</product>
			</function>
			
			
		</axis>
		
		<axis name="SIDE">
			
			<function name="aero/coefficient/CYb">
				<description>Side_force_due_to_beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/beta-rad</property>
					<!-- <value>-1</value>  -->
					<value>-0.21</value>  <!-- AVL -->
				</product>
			</function>
			
		</axis>
		
		<axis name="ROLL">
			
			<function name="aero/coefficient/Clb">
				<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>
					<!-- <value>-0.1</value> -->
					<value>-0.12</value>  <!-- AVL -->
				</product>
			</function>
			
			<function name="aero/coefficient/Clp">
				<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>-0.4</value>  -->
					<value>-0.55</value>  <!-- AVL -->
				</product>
			</function>
			
			<function name="aero/coefficient/Clr">
				<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>
					<value>0.15</value>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							  0.	 2.7  <!-- AVL 0.4 -->
							 15.	 2.7
							 20.	 2.7  <!-- important for spin entry-->
							 90.	 0.
							180.	 1.
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/coefficient/Clda">
				<description>Roll_moment_due_to_aileron</description>
				<product>
					<property>aero/qbarU-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/aileron-control-rad</property>
					<value>-0.20</value>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							  0.	 3.85  <!-- AVL 0.37-0.44 -->
							 15.	 3.85
							 20.	 1.
							 90.	 0.
							180.	 1.
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/coefficient/Cldr">
				<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>0.01</value> -->
					<value>-0.0115</value>  <!-- AVL -->
				</product>
			</function>
			
		</axis>
		
		<axis name="PITCH">
		
			<function name="aero/coefficient/Cm0">
				<description>Pitching_moment_at_zero_alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<value>0.01</value>
				</product>
			</function>
			
			<function name="aero/coefficient/Cmalpha">
				<description>Pitch_moment_due_to_alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							-180.	 0.0000
							-135.	 1.5000
							 -90.	 1.0000
							 -30.	 0.4189
							   0.	 0.0000   <!-- dCm/dAlpha = -0.8 -->
							  15.	-0.2094
							  20.	-0.2793
							  90.	-1.0000
							 135.	-1.5000
							 180.	 0.0000
						</tableData>
					</table>
				</product>
			</function>
			
			
			<function name="aero/coefficient/Cmde">
				<description>Pitch_moment_due_to_elevator</description>
				<product>
					<property>aero/qbarUUprop-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>fcs/elevator-pos-rad</property>
					<value>-1.15</value> <!-- AVL -0.39 -->
				</product>
			</function>
			
			<function name="aero/coefficient/Cmq">
				<description>Pitch_moment_due_to_pitch_rate</description>
				<product>
					<property>aero/qbarUUprop-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>velocities/q-aero-rad_sec</property>
					<!-- <value>-12</value> -->
					<value>-5.1</value> <!-- AVL -5.1 -->
				</product>
			</function>
			
			<function name="aero/coefficient/Cmadot">
				<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>-7</value> -->
					<value>-4</value>
				</product>
			</function>
			
		</axis>
		
		<axis name="YAW">
			
			<function name="aero/coefficient/Cnb">
				<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>0.12</value> -->
					<value>0.055</value> <!-- AVL -->
				</product>
			</function>
			
			<function name="aero/coefficient/Cnp">
				<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-aero-rad_sec</property>
					<value>-0.06</value>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							  0.	 1.48   <!--AVL -0.089 -->
							 15.	 1.48
							 20.	-2.
							 60.	-3.
							 90.	 0.
							180.	 1.
						</tableData>
					</table>
				</product>
			</function>
			
			<function name="aero/coefficient/Cnr">
				<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>-0.15</value> -->
					<value>-0.094</value> <!-- AVL -->
				</product>
			</function>
			
			<function name="aero/coefficient/Cndr">
				<description>Yaw_moment_due_to_rudder</description>
				<product>
					<property>aero/qbarUUprop-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<!-- <value>-0.1</value> -->
					<value>-0.054</value> <!-- AVL -->
				</product>
			</function>
			
			<function name="aero/coefficient/Cnda">
				<description>Adverse_yaw</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/aileron-control-rad</property>
					<value>0.01</value>
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
							  0.	  5.00  <!-- AVL 0.0734 -->
							 10.	  5.00  <!-- AVL 0.040 -->
							 15.	  5.00
							 18.	  5.
							 25.	 20.
							 60.	 40.
							 90.	  0.
							180.	  1.
						</tableData>
					</table>
				</product>
			</function>
			
		</axis>
		
	</aerodynamics>
	
	
	<external_reactions>
	
<!--
		<property value="0">systems/chute/chute-reef-pos-norm</property>
		<force name="chute_attach_wing_l" frame="WIND">
			<function>
				<product>
					<property>aero/qbar-psf</property>
					<property>systems/chute/chute-reef-pos-norm</property>
					<property>systems/chute/chute-size-factor</property>
					<value> 1 </value>
					<value> 700 </value>
				</product>
			</function>
			<location unit="M">
				<x>   -0.7 </x>
				<y>   -0.5 </y>
				<z>    1.2 </z>
			</location>
			<direction>
				<x>-1 </x>
				<y> 0 </y>
				<z> 0 </z>
			</direction>
		</force>
		<force name="chute_attach_wing_r" frame="WIND">
			<function>
				<product>
					<property>aero/qbar-psf</property>
					<property>systems/chute/chute-reef-pos-norm</property>
					<property>systems/chute/chute-size-factor</property>
					<value> 1 </value>
					<value> 600 </value>
				</product>
			</function>
			<location unit="M">
				<x>   -0.7 </x>
				<y>    0.5 </y>
				<z>    1.2 </z>
			</location>
			<direction>
				<x>-1 </x>
				<y> 0 </y>
				<z> 0 </z>
			</direction>
		</force>
		<force name="chute_attach_rear" frame="WIND">
			<function>
				<product>
					<property>aero/qbar-psf</property>
					<property>systems/chute/chute-reef-pos-norm</property>
					<property>systems/chute/chute-size-factor</property>
					<value> 1 </value>
					<value> 600 </value>
				</product>
			</function>
			<location unit="M">
				<x>   0.6 </x>
				<y>   0.00 </y>
				<z>   0.8 </z>
			</location>
			<direction>
				<x>-1 </x>
				<y> 0 </y>
				<z> 0 </z>
			</direction>
		</force>
-->
		<force name="hitch" frame="BODY" unit="LBS" >
			<location unit="M">
				<x> 0.0</x>  
				<y> 0.0</y>
				<z> 0.0</z>
			</location>
			<direction>
				<x>0.0</x>
				<y>0.0</y>
				<z>0.0</z>
			</direction>
		</force>
		
		<force name="banner" frame="BODY" unit="LBS" >
			<location unit="M">
				<x> 0.0</x>  
				<y> 0.0</y>
				<z> 0.0</z>
			</location>
			<direction>
				<x>0.0</x>
				<y>0.0</y>
				<z>0.0</z>
			</direction>
		</force>
		
		<force name="parachute" frame="WIND">
			<function>
				<product>
					<p>aero/qbar-psf</p>
					<pow>
						<p>fcs/parachute-pos-norm</p>
						<v>4</v>
					</pow>
					<p>/sim/model/parachute/CDxA-sqft</p>
				</product>
			</function>
			<location unit="M">
				<x>0</x>
				<y>0.0</y>
				<z>1.5</z>
			</location>
			<direction>
				<x>-1.0</x>
				<y>0.0</y>
				<z>0.0</z>
			</direction>
		</force>
		
	</external_reactions>
	
	<system file="dragonfly-instruments"/>
	<system file="dragonfly-systems"/>
	<system file="BRS"/>
	<system file="banner"/>
	
</fdm_config>
