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

<fdm_config name="CRJ700jsb" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
	
	<fileheader>
		<author> Aeromatic v 3.1.0 </author>
		<filecreationdate> 13 Jan 2016 </filecreationdate>
		<version>$Revision: 1.49 $</version>
		<description> Models a crj2. </description>
	</fileheader>
	
	<!--
		File:     crj2.xml
		Inputs:
		name:          crj2
		type:          2 engine transonic transport
		stall speed:   110.00kts
		max weight:    72750.00 lb
		length:        106.00 ft
		wing: 
		span:         76.00 ft
		area:         760.00 sq-ft
		chord:        8.17 ft
		aspect ratio: 9.30:1
		taper ratio:  1.00:1
		incidence:    2.00 degrees
		dihedral:     0.00 degrees
		sweep:        0.00 degrees
		
		no. engines:   2
		engine type:   Turbine Engine
		engine layout: aft fuselage
		
		control type:   Conventional with Yaw Damper
		
		gear type:     tricycle
		steering type: steering
		retractable?:  yes
		
		Outputs:
		wing loading:  95.72 lb/sq-ft
		payload:       9099.25 lbs
		CL-alpha:      5.76 per radian
		CL-0:          0.20
		CL-max:        2.34
		CD-0:          0.02
		K:             0.04
		Mcrit:         0.53
	-->
	
	<metrics>
		<wingarea  unit="FT2">   760.00 </wingarea>
		<wingspan  unit="FT" >    76.00 </wingspan>
		<wing_incidence>           2.00 </wing_incidence>
		<chord     unit="FT" >     8.17 </chord>
		<htailarea unit="FT2">   190.00 </htailarea>
		<htailarm  unit="FT" >    47.70 </htailarm>
		<vtailarea  unit="FT2">  152.00 </vtailarea>
		<vtailarm  unit="FT" >    47.70 </vtailarm>
		<location name="AERORP" unit="IN">
			<x>   699.60 </x>
			<y>     0.00 </y>
			<z>     0.00 </z>
		</location>
		<location name="EYEPOINT" unit="IN">
			<x>    89.04 </x>
			<y>   -30.00 </y>
			<z>    70.00 </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">  121918.78 </ixx>
		<iyy unit="SLUG*FT2">  547951.75 </iyy>
		<izz unit="SLUG*FT2">  591782.19 </izz>
		<emptywt unit="LBS" >  43499.00 </emptywt>
		<location name="CG" unit="IN">
			<x>   699.60 </x>
			<y>     0.00 </y>
			<z>   -31.80 </z>
		</location>
		<pointmass name="Payload">
			<description> 9099.25 LBS should bring model up to entered max weight </description>
			<weight unit="LBS"> 4549.62 </weight>
			<location name="POINTMASS" unit="IN">
				<x>   699.60 </x>
				<y>     0.00 </y>
				<z>   -31.80 </z>
			</location>
		</pointmass>
	</mass_balance>
	
	<propulsion>
		
		<engine file="cf34-8">
			<location unit="IN">
				<x>  1212.00 </x>
				<y>   -20.00 </y>
				<z>     0.00 </z>
			</location>
			<orient unit="DEG">
				<pitch>     0.00 </pitch>
				<roll>     0.00 </roll>
				<yaw>     0.00 </yaw>
			</orient>
			<feed> 0 </feed>
			
			<thruster file="direct">
				<sense> 1 </sense>
				<location unit="IN">
					<x>  1212.00 </x>
					<y>   -20.00 </y>
					<z>     0.00 </z>
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		
		<engine file="cf34-8">
			<location unit="IN">
				<x>  1212.00 </x>
				<y>    20.00 </y>
				<z>     0.00 </z>
			</location>
			<orient unit="DEG">
				<pitch>     0.00 </pitch>
				<roll>     0.00 </roll>
				<yaw>     0.00 </yaw>
			</orient>
			<feed> 1 </feed>
			
			<thruster file="direct">
				<sense> 1 </sense>
				<location unit="IN">
					<x>  1212.00 </x>
					<y>    20.00 </y>
					<z>     0.00 </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="IN">
				<x>   699.60 </x>
				<y>     0.00 </y>
				<z>   -31.80 </z>
			</location>
			<capacity unit="LBS"> 6717.25 </capacity>
			<contents unit="LBS"> 3358.62 </contents>
		</tank>
		<tank type="FUEL" number="1">
			<location unit="IN">
				<x>   699.60 </x>
				<y>     0.00 </y>
				<z>   -31.80 </z>
			</location>
			<capacity unit="LBS"> 6717.25 </capacity>
			<contents unit="LBS"> 3358.62 </contents>
		</tank>
		<tank type="FUEL" number="2">
			<location unit="IN">
				<x>   699.60 </x>
				<y>     0.00 </y>
				<z>   -31.80 </z>
			</location>
			<capacity unit="LBS"> 6717.25 </capacity>
			<contents unit="LBS"> 3358.62 </contents>
		</tank>
		
	</propulsion>
	
	<ground_reactions>
		
		<contact type="BOGEY" name="NOSE">
			<location unit="IN">
				<x>   165.36 </x>
				<y>     0.00 </y>
				<z>  -152.64 </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">     21825.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 10912.50 </damping_coeff>
			<max_steer unit="DEG"> 5.00 </max_steer>
			<brake_group> NONE </brake_group>
			<retractable> 1 </retractable>
		</contact>
		
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="IN">
				<x>   727.58 </x>
				<y>   -82.08 </y>
				<z>  -152.64 </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">     72750.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 36375.00 </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="IN">
				<x>   727.58 </x>
				<y>    82.08 </y>
				<z>  -152.64 </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">     72750.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 36375.00 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> RIGHT </brake_group>
			<retractable> 1 </retractable>
		</contact>
		
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="IN">
				<x>   699.60 </x>
				<y>   -38.00 </y>
				<z>   -31.80 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      72750.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 72750.00 </damping_coeff>
		</contact>
		
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="IN">
				<x>   699.60 </x>
				<y>    38.00 </y>
				<z>   -31.80 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      72750.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 72750.00 </damping_coeff>
		</contact>
		
	</ground_reactions>
	
	<system file="Systems/Propulsion.xml"/>
	<!--<system file="Thrust Reverse.xml"/>-->
	<system file="Systems/Aircraft control.xml"/>
	<system file="Systems/Landing Gear.xml"/>
	<system file="Systems/Flaps.xml"/>
	<system file="Systems/Spoilers.xml"/>
	<system file="Systems/Speedbrake.xml"/>
	
	<flight_control name="FCS: crj2">
		
	</flight_control>
	
	<aerodynamics>
		
		<axis name="LIFT">
			
			<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-rad</independentVar>
						<tableData>
							-0.20 -0.9525
							0.00  0.2000
							0.37  2.3367
							0.60  1.0547
						</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> 10.9588 </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> 3.8792 </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> 0.4269 </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>
					<property>fcs/flap-pos-deg</property>
					<value> 0.0460 </value>
				</product>
			</function>
			
			
			<function name="aero/force/Lift_spoilers">
				<description>Delta Lift due to spoilers</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/spoilers-pos-norm</property>
					<value> -0.1000 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="DRAG">
			
			<function name="aero/force/Drag_basic">
				<description>Drag at zero lift</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-1.57    1.5000
							-0.26    0.0260
							0.00    0.0200
							0.26    0.0260
							1.57    1.5000
						</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> 0.0378 </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
							0.53    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> 0.0150 </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> 0.0018 </value>
				</product>
			</function>
			
			
			<function name="aero/force/Drag_spoilers">
				<description>Drag due to spoilers</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/spoilers-pos-norm</property>
					<value> 0.0200 </value>
				</product>
			</function>
			
			<function name="aero/force/Drag_speedbrake">
				<description>Drag due to speedbrakes</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/speedbrake-pos-norm</property>
					<value> 0.1200 </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> -0.4619 </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>
					<value> -0.0000 </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> 0.5798 </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> 0.2813 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="PITCH">
			
			<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> -0.6000 </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    -1.2000
							2.0    -0.3000
						</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> -17.0000 </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> -6.0000 </value>
				</product>
			</function>
			
		</axis>
		
		<axis name="ROLL">
			
			<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>
					<value> -0.1000 </value>
				</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> -0.8459 </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>
					<value> 0.4178 </value>
				</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    0.1000
							2.0    0.0250
						</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>
			
			<function name="aero/moment/Roll_spoilers">
				<description>Roll moment due to spoilers</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/spoilers-pos-norm</property>
					<property>fcs/left-aileron-pos-rad</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
							-0.175   0.0000
							0.0     0.2400
							0.175   0.0000
						</tableData>
					</table>
				</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> 0.2899 </value>
				</product>
			</function>
			
			<function name="aero/moment/Yaw_rol_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>
					<value> -0.0269 </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> -0.3639 </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> -0.1766 </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> 0.0000 </value>
				</product>
			</function>
			
		</axis>
		
	</aerodynamics>
	
	<external_reactions>
	</external_reactions>
	
</fdm_config>
