<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="MiG-15bis" version="2.0" release="Beta"
	xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
	xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

	<fileheader>
		<author> Slavutinsky Victor, with great help from Yurik V. Nikiforoff </author>
		<filecreationdate> 2010-09-24 </filecreationdate>
		<version>$Revision: 1.20 $</version>
		<description> MiG-15bis </description>
	</fileheader>

<!--
	File:     MiG-15bis.xml
	Inputs:
	name:          MiG-15bis
	type:          single-engine transonic fighter
	max weight:    13461.525 lb
	wing span:     33.07248 ft
	length:        33.17091 ft
	wing area:     219.606 sq-ft
	gear type:     tricycle
	retractable?:  yes
	# engines:     1
	engine type:   turbine
	engine layout: middle fuselage
	yaw damper?    no

	Outputs:
	wing loading:  61.30 lb/sq-ft
	CL-alpha:      3.5 per radian
	CL-0:          0.08
	CL-max:        1
	CD-0:          0.021
	K:             0.12

	Most used data if from MiG-15bis technical documentation, book 1, on Russian

-->

	<!-- 	ARP is 25% of mean aerodynamical chord, 
		4.139-0.647+2.120*0.25=4.022
		by Fig. 117
	-->

	<metrics>
		<wingarea  unit="FT2">		221.74 </wingarea>
		<wingspan  unit="FT" >		33.07 </wingspan>
		<wing_incidence unit="DEG">	1 </wing_incidence>
		<chord     unit="FT" >		6.955 </chord>
		<htailarea unit="FT2">		32.29 </htailarea>
		<htailarm  unit="FT" >		17.395 </htailarm>
		<vtailarea unit="FT2">		43.06 </vtailarea>
		<vtailarm  unit="FT" >		14.485 </vtailarm>
		<location name="AERORP" unit="M">
			<x>	4.022 </x>
			<y>   0.00 </y>
			<z>   0.00 </z>
		</location>
		<location name="EYEPOINT" unit="M">
			<x>  2.216 </x>
			<y>   0.00 </y>
			<z>  0.798 </z>
		</location>
		<location name="VRP" unit="IN">
			<x>0</x>
			<y>0</y>
			<z>0</z>
		</location>
	</metrics>

	<!-- 	Center of mass of empty aircraft is 30.1% of mean aerodynamical chord by Tab. 25
		4.139-0.647+2.120*0.301=4.13012 by Fig. 117
		~Same poit as K 4.139-0.55 on Fig. 117
	-->

	<mass_balance>
		<ixx unit="SLUG*FT2">      5000 </ixx>
		<iyy unit="SLUG*FT2">      8452 </iyy>
		<izz unit="SLUG*FT2">     11007 </izz>
		<emptywt unit="KG" >      3680 </emptywt>
		<location name="CG" unit="M">
			<x>	4.13012 </x>
			<y>	0.00 </y>
			<z>	0.00 </z>
		</location>
	</mass_balance>

	<propulsion>

		<engine file="VK-1">
			<location unit="M">
				<x>	5.185 </x>
				<y>	0.00 </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">
			<location unit="M">
				<x>	5.185 </x>
				<y>	0.00 </y>
				<z>	0.00 </z>
			</location>
			<orient unit="DEG">
				<pitch>	0.00 </pitch>
				<roll>	0.00 </roll>
				<yaw>	0.00 </yaw>
			</orient>
			</thruster>
		</engine>


		<!--	Places of tanks is by model and some MiG internal scheme -->

		<!--	Tank 0 is fuel system imitation actually -->

		<tank type="FUEL" number="0">
			<location unit="M">
				<x>	3.293 </x>
				<y>	0.00 </y>
				<z>	0.00 </z>
			</location>1
			<capacity unit="LBS"> 10.00 </capacity>
			<contents unit="LBS"> 10.00 </contents>
		</tank>

		<!--	Tank 1 is main tank -->

		<!--	1 kg is 1/2.76 US gallons, 1/0.453 lbs
			Normal 1 tank load is 1035l, that is 828kg, 1827lbs, 300 gal
			maximum load is 1200l, that is 2119lbs, 347gal
		-->

		<tank type="FUEL" number="1">
			<location unit="M">
				<x>	3.293 </x>
				<y>	0.00 </y>
				<z>	0.00 </z>
			</location>1
			<capacity unit="LBS"> 2120.00 </capacity>
			<contents unit="LBS"> 1827.00 </contents>
		</tank>

		<!--	Tank 2 is back balance tank

			Normal 1 tank load is 138l, that is 243lbs, 40 gal
			maximum load is 200l, that is 1120kg, 353lbs, 57gal
 -->

		<tank type="FUEL" number="2">
			<location unit="M">
				<x>	6.285 </x>
				<y>	0.00 </y>
				<z>	-0.406 </z>
			</location>
			<capacity unit="LBS"> 355.00 </capacity>
			<contents unit="LBS"> 243.00 </contents>
		</tank>

		<!--	Tanks 3 and 4 is external drop tanks -->

		<tank type="FUEL" number="3">
			<location unit="M">
				<x>	4.0 </x>
				<y>	-2.644 </y>
				<z>	-0.468 </z>
			</location>
			<capacity unit="LBS"> 441.00 </capacity>
			<contents unit="LBS"> 400.00 </contents>
		</tank>

		<tank type="FUEL" number="4">
			<location unit="M">
				<x>	4.0 </x>
				<y>	2.644 </y>
				<z>	-0.468 </z>
			</location>
			<capacity unit="LBS"> 441.00 </capacity>
			<contents unit="LBS"> 400.00 </contents>
		</tank>

	<!--	Tank 5 used to count gunshell weight influence
		Weights:
			1 kg is 1/2.76 US gallons, 1/0.453 lbs
			1 N-37 shell is 0.735 kg, overall 40
			1 NS-23 shell is 0.2 kg, overall 80x2 
			So, whole weight is 
			(40*0.735+160*0.2)/0.453=135.54 lbs
			or
			(40*0.735+160*0.2)/2.76=22.24 gal_us
	-->

		<tank type="FUEL" number="5">
			<location unit="M">
				<x>	1.8</x>
				<y>	0.0 </y>
				<z>	-0.45 </z>
			</location>
			<capacity unit="LBS"> 150.00 </capacity>
			<contents unit="LBS"> 136.0 </contents>
		</tank>

	</propulsion>

<!--
spring_coeff is the spring rate, so it controls how far the model sags at rest. damping_coeff and damping_coeff_rebound control how fast the spring absorbs and releases energy
Default unit for spring rate is LBF/FT and damping is LBF/FT/S
-->

	<ground_reactions>

		<contact type="BOGEY" name="NOSE">
			<location unit="M">
				<x>	1.057 </x>
				<y>	0.00 </y>
				<z>	-1.459 </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">       8000.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  1346.15 </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="M">
				<x>	4.297 </x>
				<y>	-1.918 </y>
				<z>	-1.333 </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">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </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>	4.297 </x>
				<y>	1.918 </y>
				<z>	-1.333 </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">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </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="M">
				<x>	6.135 </x>
				<y>	-4.841 </y>
				<z>	-0.159 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x>	6.135 </x>
				<y>	4.841 </y>
				<z>	-0.159 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="NOSE_FUS">
			<location unit="M">
				<x>	0.004 </x>
				<y>	0.0 </y>
				<z>	-0.369 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="NOSE_FUS_UP">
			<location unit="M">
				<x>	0.011 </x>
				<y>	0.094 </y>
				<z>	0.473 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="MIDDLE_FUS">
			<location unit="M">
				<x>	4.080 </x>
				<y>	0.0 </y>
				<z>	-0.744 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="CABIN_FUS_UP">
			<location unit="M">
				<x>	2.259 </x>
				<y>	0.0 </y>
				<z>	1.044 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC">  2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="VSTAB">
			<location unit="M">
				<x>	9.273 </x>
				<y>	0.0 </y>
				<z>	2.516 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 2692.31 </damping_coeff>
		</contact>

		<contact type="STRUCTURE" name="BACK_FUS">
			<location unit="M">
				<x>	8.061 </x>
				<y>	0.0 </y>
				<z>	-0.281 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      13461.52 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 2692.31 </damping_coeff>
		</contact>

	</ground_reactions>

	<flight_control name="FCS: MiG-15bis">

		<property value="0.3">fcs/throttle-cmd-norm-real</property>

		<channel name="Throttle Control">

			<pure_gain name="Throttle Enchancer">
				<input>	fcs/throttle-cmd-norm-real </input>
				<gain>	1 </gain>
				<output>fcs/throttle-pos-norm</output>
			</pure_gain>

		</channel>

		<property value="0">fcs/pitch-trim-norm-real</property>

		<channel name="Pitch">

			<summer name="Pitch Trim Sum">
				<input>fcs/elevator-cmd-norm-real</input>
				<input>fcs/pitch-trim-norm-real</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>

			<kinematic name="Pitch Trim Sum Timed">
				<input>fcs/pitch-trim-sum</input>
				<traverse>
				<setting>
					<position>-1</position>
					<time>0</time>
				</setting>
				<setting>
					<position>1</position>
					<time>1</time>
				</setting>
				</traverse>
			</kinematic>

			<kinematic name="Pitch Timed">
				<input>fcs/elevator-cmd-norm</input>
				<traverse>
				<setting>
					<position>-1</position>
					<time>0</time>
				</setting>
				<setting>
					<position>1</position>
					<time>1</time>
				</setting>
				</traverse>
			</kinematic>

			<aerosurface_scale name="Elevator Rad Scale">
				<input>fcs/pitch-trim-sum-timed</input>
				<range>
					<min> -0.55 </min>
					<max>  0.28 </max>
				</range>
				<output>fcs/elevator-pos-rad</output>
			</aerosurface_scale>

			<aerosurface_scale name="Elevator Indicated Pos Rad">
				<input>fcs/pitch-timed</input>
				<range>
					<min> -0.55 </min>
					<max>  0.28 </max>
				</range>
			</aerosurface_scale>

			<aerosurface_scale name="Elevator Norm Scale">
				<input>fcs/elevator-pos-rad</input>
				<domain>
					<min> -0.55 </min>
					<max>  0.28 </max>
				</domain>
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/elevator-pos-norm</output>
			</aerosurface_scale>

		</channel>

		<property value="0">fcs/roll-trim-norm-real</property>

		<channel name="Roll">

			<pure_gain name="Aileron Cmd Norm Busted">
				<input>	fcs/aileron-cmd-norm-real </input>
				<gain>	fcs/aileron-boost </gain>]
			</pure_gain>

			<summer name="Roll Trim Sum">
				<input>fcs/aileron-cmd-norm-busted</input>
				<input>fcs/roll-trim-norm-real</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>

			<kinematic name="Roll Trim Sum Timed">
				<input>fcs/roll-trim-sum</input>
				<traverse>
				<setting>
					<position>-1</position>
					<time>0</time>
				</setting>
				<setting>
					<position>1</position>
					<time>1</time>
				</setting>
				</traverse>
			</kinematic>

			<kinematic name="Roll Timed">
				<input>fcs/aileron-cmd-norm-real</input>
				<traverse>
				<setting>
					<position>-1</position>
					<time>0</time>
				</setting>
				<setting>
					<position>1</position>
					<time>1</time>
				</setting>
				</traverse>
			</kinematic>

			<switch name="Roll Trim Sum Resulted">
				<default value="fcs/roll-trim-sum"/>
				<test value="fcs/roll-trim-sum-timed">
					fcs/aileron-boost gt 0.2
				</test>
			</switch>

			<switch name="Roll Resulted">
				<default value="fcs/aileron-cmd-norm-real"/>
				<test value="fcs/roll-timed">
					fcs/aileron-boost gt 0.2
				</test>
			</switch>

			<pure_gain name="Roll Trim Sum Echoed">
				<input>	fcs/roll-trim-sum </input>
				<gain>	1 </gain>
			</pure_gain>

			<aerosurface_scale name="Left Aileron Rad Scale">
				<input>fcs/roll-trim-sum-resulted</input>
				<range>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</range>
				<output>fcs/left-aileron-pos-rad</output>
			</aerosurface_scale>

			<aerosurface_scale name="Left Aileron Indicated Pos Rad">
				<input>fcs/roll-resulted</input>
				<range>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</range>
			</aerosurface_scale>

			<aerosurface_scale name="Right Aileron Rad Scale">
				<input>-fcs/roll-trim-sum-resulted</input>
				<range>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</range>
				<output>fcs/right-aileron-pos-rad</output>
			</aerosurface_scale>

			<aerosurface_scale name="Right Aileron Indicated Pos Rad">
				<input>-fcs/roll-resulted</input>
				<range>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</range>
			</aerosurface_scale>


			<aerosurface_scale name="Left Aileron Norm Scale">
				<input>fcs/left-aileron-pos-rad</input>
				<domain>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</domain>
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/left-aileron-pos-norm</output>
			</aerosurface_scale>

			<aerosurface_scale name="Right Aileron Norm Scale">
				<input>fcs/right-aileron-pos-rad</input>
				<domain>
					<min> -0.26 </min>
					<max>  0.26 </max>
				</domain>
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/right-aileron-pos-norm</output>
			</aerosurface_scale>

		</channel>

		<channel name="Yaw">

			<summer name="Rudder Command Sum">
				<input>fcs/rudder-cmd-norm-real</input>
				<input>fcs/yaw-trim-cmd-norm</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>

			<aerosurface_scale name="Rudder Control">
				<input>fcs/rudder-command-sum</input>
				<range>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</range>
				<output>fcs/rudder-pos-rad</output>
			</aerosurface_scale>

			<aerosurface_scale name="Rudder Normalization">
				<input>fcs/rudder-pos-rad</input>
				<domain>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</domain>	
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/rudder-pos-norm</output>
			</aerosurface_scale>

		</channel>

		<channel name="Flaps">

			<kinematic name="Flaps Control">
				<input>fcs/flap-cmd-norm-real</input>
				<traverse>
					<setting>
						<position>  0 </position>
						<time>      0 </time>
					</setting>
					<setting>
						<position> 20 </position>
						<time>      4 </time>
					</setting>
					<setting>
						<position> 55 </position>
						<time>      3 </time>
					</setting>
				</traverse>
				<output>fcs/flap-pos-deg</output>
			</kinematic>

			<aerosurface_scale name="Flap Normalization">
				<input>fcs/flap-pos-deg</input>
				<domain>
					<min>  0 </min>
					<max> 55 </max>
				</domain>
				<range>
					<min> 0 </min>
					<max> 1 </max>
				</range>
				<output>fcs/flap-pos-norm</output>
			</aerosurface_scale>

		</channel>

<!-- Gears is fully controlled by main Nasal script

		<property value="0">gear/gear-cmd-norm</property>
		<property value="0">gear/gear-pos-norm</property>

-->

		<channel name="Speedbrake">

			<kinematic name="Speedbrake Control">
				<input>fcs/speedbrake-cmd-norm-real</input>
				<traverse>
					<setting>
						<position> 0 </position>
						<time>     0 </time>
					</setting>
					<setting>
						<position> 1 </position>
						<time>     3 </time>
					</setting>
				</traverse>
				<output>fcs/speedbrake-pos-norm</output>
			</kinematic>

		</channel>

	</flight_control>

	<aerodynamics>

		<property value="1">tanks/fastened</property>

		<property value="0">gtremble/on</property>
		<property value="1">gtremble/way</property>
		<property value="0.9">gtremble/max</property>
		<property value="0.3">gtremble/step</property>
		<property value="0">gtremble/current</property>

		<property value="8.0">accelerations/Nz-max</property>

<!-- Gears is fully controlled by main Nasal script

		<property value="1.0">gear/unit[0]/pos-norm-real</property>
		<property value="1.0">gear/unit[1]/pos-norm-real</property>
		<property value="1.0">gear/unit[2]/pos-norm-real</property>

-->

		<!-- Fig 51, 52-->
		<function name="calculations/aero/coefficient/liftalphaflapnorm">
			<description>Lift_due_to_alpha_and_flaps_normalised</description>
			<table>
			<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
			<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
			<tableData>
					0.0	20	55
				-0.104	-0.53	-0.33	-0.08
				0.0	-0.05	0.1	0.037
				0.174	0.67	0.87	0.113
				0.209	0.82	1.02	0.125
				0.244	0.96	1.14	0.137
				0.279	1.09	1.26	0.146
				0.314	1.12	1.22	0.135
				0.349	1.11	1.19	0.129
				0.383	1.12	1.16	0.127
			</tableData>
			</table>
		</function>

		<axis name="LIFT">

			<!-- Fig 51, 52-->
			<function name="aero/coefficient/CLalphaflaps">
				<description>Lift_due_to_alpha_and_flaps</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
				<tableData>
						0.0	20	55
					-0.104	-0.53	-0.33	-0.08
					0.0	-0.05	0.1	0.37
					0.174	0.67	0.87	1.13
					0.209	0.82	1.02	1.25
					0.244	0.96	1.14	1.37
					0.279	1.09	1.26	1.46
					0.314	1.12	1.22	1.35
					0.349	1.11	1.19	1.29
					0.383	1.12	1.16	1.27
				</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 59, from  0.2 deg to 1.05 deg, step 0.05 deg-->
			<function name="aero/coefficient/dCLalphamach">
				<description>Delta_Lift_due_to_alpha_and_mach</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<table>
					<independentVar lookup="column">aero/alpha-wing-rad</independentVar>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
						-0.5	1.5	3	4.5	6	9
					0.0034	0.0	0.0	0.0	0.0	0.0	0.0
					0.0043	0.0	0.001	0.005	0.005	0.01	0.01
					0.0052	0.0	0.003	0.01	0.01	0.015	0.02
					0.0061	0.0	0.005	0.015	0.015	0.02	0.025
					0.0069	0.0	0.007	0.02	0.02	0.025	0.03
					0.0078	0.0	0.009	0.025	0.025	0.03	0.035
					0.0087	0.0	0.01	0.03	0.03	0.035	0.04
					0.0095	0.0	0.011	0.035	0.04	0.04	0.045
					0.0104	0.0	0.013	0.04	0.05	0.05	0.06
					0.0113	0.0	0.015	0.045	0.06	0.06	0.08
					0.0122	0.0	0.017	0.05	0.07	0.07	0.1
					0.0130	0.0	0.019	0.06	0.08	0.09	0.16
					0.0139	0.0	0.02	0.08	0.1	0.12	0.18
					0.0148	-0.01	0.03	0.1	0.12	0.14	0.14
					0.0157	-0.02	0.02	0.05	0.1	0.12	0.1
					0.0165	-0.04	-0.03	0.02	0.05	0.08	0.1
					0.0174	-0.03	-0.005	0.03	0.07	0.09	0.1
					0.0183	-0.03	0.0	0.05	0.1	0.10	0.1
				</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 51 inverted-->
			<function name="aero/coefficient/dCLsb">
				<description>Delta_Lift_due_to_speedbrake</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>fcs/speedbrake-pos-norm</property>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<tableData>
					0.0	0.02
					0.174	0.03
					0.209	0.04
					0.244	0.05
					0.279	0.07
					0.314	0.1
					0.383	0.1
				</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 51 -->

			<function name="aero/coefficient/dCLgearOne">
				<description>Delta_Lift_due_to_gear_one</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>gear/unit[0]/pos-norm-real</property>
				<value>0.2</value>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<tableData>
					0.0	-0.02
					0.174	-0.03
					0.209	-0.04
					0.244    -0.05
					0.279    -0.07
					0.314    -0.1
					0.383    -0.1
				</tableData>
				</table>
				</product>
			</function>

			<function name="aero/coefficient/dCLgearTwo">
				<description>Delta_Lift_due_to_gear_two</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>gear/unit[1]/pos-norm-real</property>
				<value>0.4</value>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<tableData>
					0.0	-0.02
					0.174	-0.03
					0.209	-0.04
					0.244    -0.05
					0.279    -0.07
					0.314    -0.1
					0.383    -0.1
				</tableData>
				</table>
				</product>
			</function>

			<function name="aero/coefficient/dCLgearThree">
				<description>Delta_Lift_due_to_gear_three</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>gear/unit[2]/pos-norm-real</property>
				<value>0.4</value>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<tableData>
					0.0	-0.02
					0.174	-0.03
					0.209	-0.04
					0.244    -0.05
					0.279    -0.07
					0.314    -0.1
					0.383    -0.1
				</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 53 -->
			<function name="aero/coefficient/dCLtanks">
				<description>Delta_Lift_due_to_fuel_tanks</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>tanks/fastened</property>
				<table>
				<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
				<tableData>
					0.0	-0.03
					0.174	-0.03
					0.209	-0.03
					0.244    -0.05
					0.279    -0.1
					0.314    -0.11
					0.349    -0.09
					0.383    -0.09
				</tableData>
				</table>
				</product>
			</function>

			<!-- Commented out aeromatic stuff. No more needed tweak  -->

<!--

			<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>
-->

			<!-- Need to add delta lift due to fuel tanks -->

		</axis>

		<axis name="DRAG">

			<!-- Fig 51, 52-->
			<function name="aero/coefficient/CDliftflap">
				<description>Drag_due_to_lift_coefficient_and_flaps</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<table>
					<independentVar lookup="row">calculations/aero/coefficient/liftalphaflapnorm</independentVar>
					<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
				<tableData>
						0.0	20.0	55.0
					0.0	0.018	0.03	0.084
					0.1	0.019	0.031	0.085
					0.2	0.02	0.032	0.086
					0.3	0.022	0.034	0.087
					0.4	0.026	0.038	0.088
					0.5	0.034	0.043	0.09
					0.6	0.043	0.05	0.096
					0.7	0.053	0.06	0.106
					0.8	0.066	0.07	0.112
					0.9	0.082	0.082	0.124
					1.0	0.092	0.098	0.138
					1.1	0.122	0.116	0.152
					1.2	0.122	0.128	0.172
					1.3	0.122	0.168	0.190
					1.4	0.122	0.168	0.218
					1.5	0.122	0.168	0.250
				</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>0.12</value>
				</product>
			</function>

			<!-- Fig 57. Speeds are 500, 700, 800, 900 1000km\h -->
			<function name="aero/coefficient/CDmachalt">
				<description>Drag_due_to_speed_and_altitude</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<table>
					<independentVar lookup="row">velocities/vc-kts</independentVar>
					<independentVar lookup="column">position/h-agl-ft</independentVar>
					<tableData>
							0.0	16404.0	32808.0	49212.0
						0.0	0.0013	0.0043	0.0143	0.0648
						269.9	0.0013	0.0043	0.0143	0.0648
						377.9	0.0003	0.0023	0.0075	0.0301
						431.9	0.0	0.0018	0.0055	0.0195
						485.9	0.0008	0.0023	0.0055	0.0165
						539.9	0.0013	0.0035	0.0208	0.0648
					</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 51, 58 -->
			<function name="aero/coefficient/CDgear">
				<description>Drag_due_to_gear</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>gear/gear-pos-norm</property>
				<table>
				<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
					0.0	0.02
					0.2	0.022
					0.3	0.0221
					0.4	0.0225
					0.5	0.023
					0.6	0.0235
					0.7	0.025
					0.8	0.027
					0.9	0.03
					1.0	0.0337
					1.1	0.0373
				</tableData>
				</table>
				<value> 0.25 </value>
				</product>
			</function>

			<!-- Fig 51, 53 -->
			<function name="aero/coefficient/CDtank">
				<description>Drag_due_to_fuel_tanks</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>tanks/fastened</property>
				<table>
				<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
					0.0	0.02
					0.2	0.022
					0.3	0.0221
					0.4	0.0225
					0.5	0.023
					0.6	0.0235
					0.7	0.025
					0.8	0.027
					0.9	0.03
					1.0	0.0337
					1.1	0.0373
				</tableData>
				</table>
				<value> 0.2 </value>
				</product>
			</function>

			<!-- Fig 58 -->
			<function name="aero/coefficient/CDsb">
				<description>Drag_due_to_speedbrakes</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>fcs/speedbrake-pos-norm</property>
				<table>
				<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
					0.0	0.02
					0.2	0.022
					0.3	0.0221
					0.4	0.0225
					0.5	0.023
					0.6	0.0235
					0.7	0.025
					0.8	0.027
					0.9	0.03
					1.0	0.0337
					1.1	0.0373
				</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<function name="aero/coefficient/CDbeta">
				<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       1.230
					-0.26    0.050
					0.00       0.000
					0.26    0.050
					1.57       1.230
				</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>0.01</value>
				</product>
			</function>

			<!-- Need to add drag due to fuel tanks -->

		</axis>

		<axis name="SIDE">

			<!-- Fig 76 -->
			<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>-0.074</value>
				</product>
			</function>

		</axis>

		<!-- Adition by the book, page 72, text -->
		<function name="fcs/left-aileron-pos-deg-mod">
			<description>Aileron_modified_due_mach_and_altitude_and_high_g_tremble</description>
			<sum>
				<property>fcs/left-aileron-pos-deg</property>
				<property>gtremble/current</property>
				<table>
					<independentVar lookup="column">position/h-agl-ft</independentVar>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
						6561.67	9842.51	32808.3	36089.23
					0.86	0.0	0.0	0.0	0.0
					0.88	6.0	0.0	0.0	0.0
					0.9	12.0	0.0	0.0	0.0
					0.92	18.0	0.0	0.0	6.0
					0.94	18.0	0.0	0.0	12.0
					0.96	18.0	0.0	0.0	18.0
				</tableData>
				</table>
			</sum>
		</function>

		<axis name="ROLL">

			<!-- Fig 68 -->
			<function name="aero/coefficient/Clbflap">
				<description>Roll_moment_due_to_beta_and_flaps</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/bw-ft</property>
				<table>
				<independentVar lookup="row">aero/beta-rad</independentVar>
				<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
				<tableData>
						0.0	55.0
					-0.174	0.016	0.033
					0.0	0.0	0.0
					0.174	-0.016	-0.033
				</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>
				</product>
			</function>

			<!-- Fig 72, 179 -->
			<function name="aero/coefficient/Cldamach">
				<description>Roll_moment_due_to_aileron_and_mach</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/bw-ft</property>
				<table>
					<independentVar lookup="column">fcs/left-aileron-pos-deg-mod</independentVar>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
						-14	-12	-8	-4	0	4	8	12	14
					0.0	0.0	0.0	0.0	0.0	0	0.0	0.0	0.0	0.0
					0.2	-0.022	-0.017	-0.0125	-0.006	0	0.006	0.0125	0.017	0.022
					0.80	-0.022	-0.017	-0.0125	-0.006	0	0.006	0.0125	0.017	0.022
					0.82	-0.02	-0.017	-0.0125	-0.006	0	0.006	0.0125	0.017	0.02
					0.86	-0.022	-0.018	-0.0125	-0.006	0	0.006	0.0125	0.018	0.022
					0.88	-0.018	-0.016	-0.012	-0.008	0	0.008	0.012	0.016	0.018
					0.9	-0.016	-0.014	-0.011	-0.008	0	0.008	0.011	0.014	0.016
					0.92	-0.014	-0.012	-0.009	-0.007	0	0.007	0.009	0.012	0.014
					0.94	-0.013	-0.01	-0.008	-0.007	0	0.007	0.008	0.01	0.013
					0.96	-0.011	-0.009	-0.008	-0.007	0	0.007	0.008	0.009	0.011
				</tableData>
				</table>
					<value>5.81</value>
				<table>
				<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
					0.0	0.0
					0.30	0.172
					0.40	0.168
					0.50	0.164
					0.60	0.160
					0.70	0.150
					0.80	0.126
					0.86	0.102
					0.9	0.082
					0.92	0.054
					0.94	0.000
					0.96	-0.06
					0.98	-0.05
				</tableData>
				</table>
				</product>
			</function>

			<!-- Basicly Aeromatic stuff, data not included in MiG documentation,
				but Mach addition, Fig 42-->
			<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>
				<table>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
					0.4	3.0
					0.5	2.9
					0.6	2.7
					0.7	2.3
					0.8	1.4
					0.825	0.8
					0.85	0.3
					0.875	-0.9
					0.9	-1.3
					0.925	-1.2
					0.95	-0.4
					0.975	0.7
					1.0	1.5
				</tableData>
				</table>
				<value>0.3333</value>
				</product>
			</function>

			<!-- Roll due to fuel tanks can be avoided-->

		</axis>

		<property value="40">weights/shells/n37</property>
		<property value="80">weights/shells/n23-inner</property>
		<property value="80">weights/shells/n23-outer</property>

		<function name="calculations/pitch-weights-delta/mass-center-m">
		<product>
			<value>0.0254</value><!--To convert from inches to meters -->
			<property>inertia/cg-x-in</property>
		</product>
		</function>

		<function name="calculations/pitch-weights-delta/mass-center-shift-m">
		<sum>
			<value>-4.13012</value>
			<property>calculations/pitch-weights-delta/mass-center-m</property>
		</sum>
		</function>

		<function name="calculations/pitch-weights-delta/mass-center-shift-ft">
		<product>
			<value>3.2808</value><!--1/0.3048 to convert from meters to feets-->
			<property>calculations/pitch-weights-delta/mass-center-shift-m</property>
		</product>
		</function>

		<axis name="PITCH">

			<!-- Fig 169 
			<function name="fcs/elevator-pos-rad-mod">
				<description>Elevator_modified_due_mach_and_altitude</description>
				<sum>
					<property>fcs/elevator-pos-rad</property>
					<product>
						<value>-0.01745329</value>
						<table>
							<independentVar lookup="column">position/h-agl-ft</independentVar>
							<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
								7545.93		18044.61		35433.07
							0.20	-10		-10.0			-7.6
							0.30	-2.3		-7.0			-7.6
							0.40	0.2		-2.0			-7.6
							0.50	1.6		-0.2			-4.6
							0.60	2.4		1.0			-2.2
							0.70	3.0		1.8			-0.4
							0.80	3.2		2.4			0.2
							0.82	3.2		2.5			0.2
							0.84	3.2		2.4			0.3
							0.86	3.1		2.3			0.3
							0.88	3.1		2.2			0.4
							0.90	3.0		1.8			0.2
							0.92	3.4		1.7			-0.4
							0.94	4.6		2.8			0.1
							0.96	5.6		4.0			2.0
							0.98	6.8		5.2			3.2
							1.00	7.2		5.6			4.0
						</tableData>
						</table>
					</product>
				</sum>
			</function>

-->

			<!-- 
				Delta pitch due to weight diffrence, page 26
				Common formulae is Mz=Mznorm+(CMw-CMnorm)*Cynorm,
				so delta is Cynorm*(CMw-CMnorm),
				Length of mean aoerodynamical horde is is 2.120 m
				Center of mass of empty aircraft is 4.13012 m
				Need to convert it to feets, though.
			-->

			<function name="aero/coefficient/Cmwddp">
			<description>Pitch_moment_due_to_weight diffrence</description>
			<product>
				<property>aero/coefficient/CLalphaflaps</property>
				<property>calculations/pitch-weights-delta/mass-center-shift-ft</property>
			</product>
			</function>

			<!-- Fig 63 -->
			<function name="aero/coefficient/Cmalphaelev">
				<description>Pitch_moment_due_to_alpha_and_elevator</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/cbarw-ft</property>
				<table>
					<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
					<independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
					<tableData>
						-0.349	-0.174	-0.087	0.0	0.087
					-0.034	0.21	0.135	0.082	0.037	-0.013
					0.0	0.2	0.12	0.07	0.022	-0.023
					0.034	0.19	0.102	0.053	0.007	-0.042
					0.069	0.175	0.087	0.04	-0.007	-0.058
					0.104	0.162	0.073	0.025	-0.022	-0.071
					0.139	0.15	0.057	0.009	-0.04	-0.086
					0.174	0.137	0.042	-0.005	-0.057	-0.103
					0.209	0.123	0.027	-0.02	-0.069	-0.118
					0.224	0.11	0.013	-0.037	-0.085	-0.132
					0.279	0.093	-0.002	-0.052	-0.097	-0.148
					0.314	0.09	0.002	-0.049	-0.097	-0.142
					0.349	0.045	-0.02	-0.062	-0.104	-0.15
					0.383	0.01	-0.08	-0.099	-0.131	-0.17
					</tableData>
				</table>
				</product>
			</function>

			<!-- Fig 66 
			<function name="aero/coefficient/dCmmach">
				<description>Delta_pitch_moment_due_to_mach</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/cbarw-ft</property>
				<table>
					<independentVar lookup="column">fcs/elevator-pos-deg</independentVar>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
						-10	-8	-6 	-4	-2	0	2	4
					0.2	0.0	0.0	0.0	0.0	0.0	0.0	0.0	0.0
					0.80	0.0	0.0	0.0	0.0	0.0	0.0	0.0	0.0
					0.84	0.004	0.004	0.004	0.004	0.004	0.004	0.004	0.004
					0.88	0.005	0.005	0.005	0.005	0.005	0.005	0.005	0.005
					0.90	0.006	0.007	0.008	0.008	0.008	0.009	0.009	0.011
					0.92	0.014	0.015	0.016	0.017	0.018	0.018	0.019	0.02
					0.94	0.026	0.027	0.028	0.029	0.03	0.032	0.034	0.036
					0.96	0.028	0.031	0.034	0.038	0.04	0.043	0.046	0.05
					0.98	0.022	0.027	0.032	0.037	0.042	0.047	0.052	0.06
					1.0	0.01	0.02	0.03	0.04	0.05	0.06	0.06	0.06
					1.02	0.0	0.01	0.02	0.028	0.036	0.044	0.044	0.044
				</tableData>
				</table>
				</product>
			</function>

			-->

			<!-- Fig 65 -->

			<function name="aero/coefficient/dCmmach">
				<description>Delta_pitch_moment_due_to_mach</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/cbarw-ft</property>
				<table>
					<independentVar lookup="column">calculations/aero/coefficient/liftalphaflapnorm</independentVar>
					<independentVar lookup="row">velocities/mach</independentVar>
				<tableData>
						0	0.1	0.2	0.3	0.4	0.5	0.6	0.7
					0.0	0.0	0.0	0.0	0.0	0.0	0.0	0.0	0.0
					0.2	0.0	0.0	0.0	0.0	0.0	0.0	0.0	0.0
					0.4	0.004	0.004	0.005	0.005	0.005	0.005	0.005	0.005
					0.6	0.004	0.005	0.005	0.006	0.007	0.01	0.015	0.022
					0.7	0.005	0.006	0.01	0.012	0.012	0.015	0.022	0.03
					0.74	0.005	0.007	0.01	0.012	0.016	0.02	0.028	0.035
					0.8	0.006	0.008	0.01	0.012	0.014	0.019	0.025	0.03
					0.82	0.007	0.009	0.012	0.014	0.012	0.018	0.02	0.022
					0.84	0.008	0.009	0.01	0.009	0.008	0.007	0.005	0.003
					0.86	0.012	0.011	0.007	0.005	0.003	0.0	-0.005	-0.01
					0.88	0.018	0.015	0.012	0.006	0.002	-0.008	-0.016	-0.02
					0.9	0.023	0.018	0.016	0.005	-0.004	-0.012	-0.026	-0.04
					0.92	0.03	0.025	0.018	0.008	-0.005	-0.012	-0.028	-0.045
					0.94	0.042	0.036	0.025	0.016	0.005	-0.012	-0.026	-0.042
					0.96	0.05	0.045	0.032	0.025	0.01	-0.015	-0.035	-0.055
					0.98	0.06	0.05	0.038	0.03	0.008	-0.025	-0.055	-0.075
					1.0	0.065	0.05	0.04	0.028	0.0	-0.04	-0.08	-0.115
					1.02	0.065	0.045	0.035	0.02	-0.01	-0.045	-0.09	-0.13
				</tableData>
				</table>
				</product>
			</function>


			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<function name="aero/coefficient/Cmq">
				<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>-18</value>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>-9</value>
				</product>
			</function>

			<!-- Fig 63, 64 -->
			<function name="aero/coefficient/Cmflap">
				<description>Pitch_moment_due_to_flaps</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/cbarw-ft</property>
				<table>
					<independentVar lookup="row">fcs/flap-pos-deg</independentVar>
					<tableData>
					0.0	0.0
					55.0	-0.04
					</tableData>
				</table>
				</product>
			</function>

			<!-- Need to add pitch due to fuel tanks-->

		</axis>

		<!-- High g tremble yaw modification, page 73 -->
		<function name="fcs/rudder-pos-deg-mod">
			<description>Rudder_angle_modified_due_to_high_g_tremble</description>
			<sum>
				<property>fcs/rudder-pos-deg</property>
				<property>gtremble/current</property>
			</sum>
		</function>

		<axis name="YAW">

			<!-- Fig 73 -->
			<function name="aero/coefficient/Cnbflap">
				<description>Yaw_moment_due_to_beta_and_flaps</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/bw-ft</property>
				<table>
					<independentVar lookup="row">aero/beta-deg</independentVar>
					<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
					<tableData>
						0.0	55.0
					-16	-0.042	-0.046
					-14	-0.033	-0.041
					-12	-0.025	-0.034
					-10	-0.018	-0.028
					-8	-0.014	-0.023
					-6	-0.011	-0.017
					-4	-0.006	-0.012
					-2	-0.003	-0.006
					0	0	0
					2	0.003	0.006
					4	0.006	0.012
					6	0.011	0.017
					8	0.014	0.023
					10	0.018	0.028
					12	0.025	0.034
					14	0.033	0.041
					16	0.042	0.046
					</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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>
				</product>
			</function>

			<!-- Fig 75 -->
			<function name="aero/coefficient/Cndr">
				<description>Yaw_moment_due_to_rudder</description>
				<product>
				<property>aero/qbar-psf</property>
				<property>metrics/Sw-sqft</property>
				<property>metrics/bw-ft</property>
				<table>
				<independentVar lookup="row">fcs/rudder-pos-deg-mod</independentVar>
				<tableData>
					-17	0.022
					0	0
					17	-0.022
				</tableData>
				</table>
				</product>
			</function>

			<!-- Aeromatic stuff, data not included in MiG documentation -->
			<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/left-aileron-pos-rad</property>
				<value>0</value>
				</product>
			</function>

			<!-- Yaw due to mach can be avoided-->
			<!-- Yaw due to fuel tanks can be avoided-->

		</axis>

	</aerodynamics>

	<system file="Click">
	</system>

	<system file="Airspeedometer">
	</system>

	<system file="Arthorizon">
	</system>

	<system file="Headsight">
	</system>

	<system file="Tachometer">
	</system>

	<system file="Gascontrol">
	</system>

	<system file="Flapscontrol">
	</system>

	<system file="Canopy">
	</system>

	<system file="Accchecker">
	</system>

	<system file="Rightpanel">
	</system>

	<system file="Stopcontrol">
	</system>

	<system file="Leftpanel">
	</system>

	<system file="Ignitionbutton">
	</system>

	<system file="Speedbrakescontrol">
	</system>

	<system file="Fuelcontrol">
	</system>

	<system file="Vertspeedometer">
	</system>

	<system file="Gearcontrol">
	</system>

	<system file="Radioaltimeter">
	</system>

	<system file="Stick">
	</system>

	<system file="Pedals">
	</system>

	<system file="Gearvalve">
	</system>

	<system file="Flapsvalve">
	</system>

	<system file="Radiocompass">
	</system>

	<system file="Boostercontrol">
	</system>

	<system file="Gyrocompass">
	</system>

	<system file="Altimeter">
	</system>

</fdm_config>
