# Aircraft Inventory for ACM 5.0
# See ACM-Bibliography for further information about the sources of this
# information.

# Mig-29 Fulcrum
# MiG-29M information was derived from two sources: [Spick87] and [AirI Aug92].

aircraft "MiG-29" {

	Description "Mikoyan-Guryevich MiG-29M Fulcrum"
	Object		"mig29.obv"
	WingArea	400.0	# (wingS) Wing surface area (ft^2)
	WingHalfSpan	18.87	# (wings) Wing half-span (ft)
	Chord		9.61	# (c) Mean geometric chord of wing (ft)
	AspectRatio	3.56	# (aspectRatio) aspect ratio
	EmptyWeight	22500.0	#(emptyWeight) Empty weight (lb)
	
	DISEntityType	 1:2:222:1:2:5:0
	DISAltEntityType 1:2:225:1:3:3:0

	# (I(x,y,z)) Moments of inertia
	Ixx		10000.0
	Iyy		75000.0
	Izz		80000.0

	# (cFlap) Lift due to flaps (yields Clift of 1.0 at max extension)
	CFlap		0.64279
	CLNegStall	17.0	# (deg)
	CLPosStall	30.0	# (deg)
	BetaStall	15.0	# (deg)

	CFlapDrag	0.0467	# (cFlapDrag) Drag due to Flaps
	CGearDrag	0.03	# (cGearDrag) Drag due to Gear
	CSpeedBrake	0.03	# (cSpeedBrake) Drag due to Speed Brake
				# at 90 degrees

	# (CDb) Drag Characteristic equation [Wave+body]
	# independent variable is mach number
	CDb	{		# (CDb) Drag Characteristic equation [Wave+body]
				# independent variable is mach number
		0.0,	0.020,
		0.2,	0.020,
		0.95,	0.015,
		1.05,	0.045,
		2.00,	0.030,
		10.0,	0.030
		}

	CLift	{		# (CLift) Lift-slope curve (vs alpha)
		-3.0,	0.0,
		-1.05,	0.0,
		-0.576,	-2.199,
		-0.556,	-2.23,
		-0.524, -2.199,
		0.524,	2.199,
		0.556,	2.23,
		0.576,	2.199,
		1.05,	0.0,
		2.0,	0.0
		}

	CnBeta	{		# (CnBeta) Yaw due to sideslip equation
		0,	-0.08125,
		0.523540, -0.078125,
		0.785340, -0.0609375,
		1.047198, 0.125,
		1.58,	0.0
		}

	ClBeta	{		# (ClBeta) Roll due to sideslip equation 
		0,	-0.0125,
		0.43633, -0.015,
		0.78540, 0.125,
		1.58,	0.0,
		3.142,	0.125,
		}

	CDBOrigin	0	# (CDBOrigin, CDBFactor) Drag due to sideslip
	CDBFactor	0.5	
	CDBPhase	0	# (CDBPhase) sideslip drag phase (deg)
	CYBeta		-1.4	# (CYbeta) Side-force from side-slip [dCY/dBeta]
	EffElevator	0.60	# (effElevator) Elevator effectiveness
	EffRudder	0.14	# (effRudder) Rudder effectiveness
	MaxRudder	20	# (maxRudder) max Rudder (deg)
	SeTrimTakeoff	0	# (SeTrimTakeoff) Elevator trim at takeoff (deg)
	MaxAileron	20	# (maxAileron) max Aileron (deg)
	MaxFlap		20	# (maxFlap) max flap setting (deg)
	# (flapRate) flap extension rate (about 2 secs to fully extend flaps)
	FlapRate	10	# (deg/sec)
	# (gearRate) gear extension rate (about 3 secs to fully extend gear)
	GearRate	30	# (deg/sec)
	MaxSpeedBrake	80	# (maxSpeedBrake) max Speed Brake setting (deg)
	# (speedBrakeRate) rate of speed brake extension (2 secs to full ext)
	SpeedBrakeRate	40	# (deg/sec)
	# (speedBrakeIncr) speed Brake increment per keystroke
	SpeedBrakeIncr	80	# (deg)
	Clda		0.048	# (Clda) roll moment from aileron offset
	Cldr		0.004	# (Cldr) roll moment from rudder offset
	Clp		-0.27	# (Clp) roll damping
	Cmq		-8.0	# (Cmq) pitch damping factor
	Cnr		-0.378	# (Cnr) yaw damping factor
	CmAlpha		-0.40	# (cmSlope) CmAlpha curve slope 
	CmFactor	-0.20	# (cmFactor) CmAlpha factor when stalled 
	MaxFuel		9750	# (maxFuel) maximum internal fuel (lb)
	# engine lag factor (how fast does it respond to throttle changes)
	EngineLag	-3.0
	# Engine data based on updated RD-33K engines cited in [AirI Aug89].
	# (maxThrust) max static thrust, military power (lb) 
	MaxThrust	27000
	# (maxABThrust) max static thrust, afterburner on  (lb) 
	MaxABThrust	44000

	Thrust	{		# (Thrust) Mach Number vs. thrust	
		0,	1,
		1.7,	1.5,
		2.0,	0.84,
		5,	0.5
		}
	ABThrust {		# (ABThrust) afterburner thrust table
		0,	1,
		0.5,	1,
		1,	1.21,
		1.7,	1.7,
		5,	1.64
		}
	# (spFuelConsump) specific fuel consump(lb fuel/lb T x hr)
	SpFuelConsump	0.68
	# (spABFuelConsump) AB specific fuel consump(lb fuel/lb T x hr)
	SpABFuelConsump	2.55
	# (groundingPoint) hypothetical single pt of contact w/ground 
	GroundingPoint	{ 0,  0,  6.5 }
	# (viewPoint) pilot's viewing location wrt CG
	ViewPoint	{ 14.75, 0,  -5.375 }

	# Landing Gear control parameters

	MuStatic	0.08	# (muStatic) static coeff of friction no-brakes 
	MuKinetic	0.05	# (muKinetic) moving coeff of friction no-brakes
	MuBStatic	0.7	# (muBStatic) static brakes-on
	MuBKinetic	0.6	# (muBKinetic) moving brakes-on

	MaxNWDef	72	# (maxNWDef) maximum nosewheel deflection (deg)
	NWIncr		0.0397	# (NWIncr) deflection for each unit (1.27/32)
	MaxNWS		85	# (maxNWS) maximum NWS velocity (fps)

	# (rm) location of main gear attachments
	Rm		{ -1.206000, 0.000000, 4.25 }
	# (rn) location of nose gear attachments
	Rn		{ 10.395000,  0.000000, 4.5 }
	Dm		10000	# main oleo damping factor
	Dn		1000	# nose oleo damping factor
	Km		105561	# main oleo spring factor
	Kn		23439.1	# nose oleo spring factor
	Gm		1.5	# main strut length with tire (ft)
	Gn		1.5	# nose strut length with tire (ft)
	CmMax		1.0	# (cmMax) main max oleo extension distance (ft)
	CnMax		0.75	# (cnMax) nose max oleo extension distance (ft)
	# (tailExtent) as we rotate, this part may drag 
	TailExtent	{ -18.165,  0.0,  1.191 }
	StructurePoints	15	# (structurePts) maximum structural damage 

	# Radar data based on N-019 Pulse Doppler radar cited in [AirI Aug89].

	RadarOutput	15000	# (radarOutput) radar output (watts)
	RadarTRange	38	# (radarTRange) tracking radar range (nm)
	RadarDRange	55	# (radarDRange) detection radar range (nm)
	TEWSThreshold	0	# Radar Warning Receiver threshold (watts)

	# Weapons

	WeaponCount	7

	HardPoint0	{ 7.0, -4.0, 0.0 }
	HardPoint1	{ 0.357, 15.6, 0.0 }
	HardPoint2	{ 0.357, -15.6, 0.0 }
	HardPoint3	{ 1.5, 9.0, 2.0 }
	HardPoint4	{ 1.5, -9.0, 2.0 }
	HardPoint5	{ 1.5, 8.0, 1.5 }
	HardPoint6	{ 1.5, -8.0, 1.5 }
	HardPoint7	{ 1.5, 10.0, 1.5 }
	HardPoint8	{ 1.5, -10.0, 1.5 }

	WeaponStation	0 "m61a1"	500	0	0
	WeaponStation	1 "aim9m"	0	0	0
	WeaponStation	2 "aim9m"	0	0	0
	WeaponStation	3 "aim9m"	0	0	0
	WeaponStation	4 "aim9m"	0	0	0
	WeaponStation	5 "aim9m"	0	0	0
	WeaponStation	6 "aim9m"	0	0	0

	}

aircraft "Su-30" {

# COVER
	
	WingArea	400.0	# (wingS) Wing surface area (ft^2)
	WingHalfSpan	18.87	# (wings) Wing half-span (ft)
	Chord		9.61	# (c) Mean geometric chord of wing (ft)
	AspectRatio	3.56	# (aspectRatio) aspect ratio
	EmptyWeight	22500.0	#(emptyWeight) Empty weight (lb)
	
	DISEntityType	 1:2:222:1:2:5:0
	DISAltEntityType 1:2:225:1:3:3:0

	# (I(x,y,z)) Moments of inertia
	Ixx		10000.0
	Iyy		75000.0
	Izz		80000.0

	# (cFlap) Lift due to flaps (yields Clift of 1.0 at max extension)
	CFlap		0.64279
	CLNegStall	17.0	# (deg)
	CLPosStall	30.0	# (deg)
	BetaStall	15.0	# (deg)

	CFlapDrag	0.0467	# (cFlapDrag) Drag due to Flaps
	CGearDrag	0.03	# (cGearDrag) Drag due to Gear
	CSpeedBrake	0.03	# (cSpeedBrake) Drag due to Speed Brake
				# at 90 degrees

	# (CDb) Drag Characteristic equation [Wave+body]
	# independent variable is mach number
	CDb	{		# (CDb) Drag Characteristic equation [Wave+body]
				# independent variable is mach number
		0.0,	0.020,
		0.2,	0.020,
		0.95,	0.015,
		1.05,	0.045,
		2.00,	0.030,
		10.0,	0.030
		}

	CLift	{		# (CLift) Lift-slope curve (vs alpha)
		-3.0,	0.0,
		-1.05,	0.0,
		-0.576,	-2.199,
		-0.556,	-2.23,
		-0.524, -2.199,
		0.524,	2.199,
		0.556,	2.23,
		0.576,	2.199,
		1.05,	0.0,
		2.0,	0.0
		}

	CnBeta	{		# (CnBeta) Yaw due to sideslip equation
		0,	-0.08125,
		0.523540, -0.078125,
		0.785340, -0.0609375,
		1.047198, 0.125,
		1.58,	0.0
		}

	ClBeta	{		# (ClBeta) Roll due to sideslip equation 
		0,	-0.0125,
		0.43633, -0.015,
		0.78540, 0.125,
		1.58,	0.0,
		3.142,	0.125,
		}

	CDBOrigin	0	# (CDBOrigin, CDBFactor) Drag due to sideslip
	CDBFactor	0.5	
	CDBPhase	0	# (CDBPhase) sideslip drag phase (deg)
	CYBeta		-1.4	# (CYbeta) Side-force from side-slip [dCY/dBeta]
	EffElevator	0.60	# (effElevator) Elevator effectiveness
	EffRudder	0.14	# (effRudder) Rudder effectiveness
	MaxRudder	20	# (maxRudder) max Rudder (deg)
	SeTrimTakeoff	0	# (SeTrimTakeoff) Elevator trim at takeoff (deg)
	MaxAileron	20	# (maxAileron) max Aileron (deg)
	MaxFlap		20	# (maxFlap) max flap setting (deg)
	# (flapRate) flap extension rate (about 2 secs to fully extend flaps)
	FlapRate	10	# (deg/sec)
	# (gearRate) gear extension rate (about 3 secs to fully extend gear)
	GearRate	30	# (deg/sec)
	MaxSpeedBrake	80	# (maxSpeedBrake) max Speed Brake setting (deg)
	# (speedBrakeRate) rate of speed brake extension (2 secs to full ext)
	SpeedBrakeRate	40	# (deg/sec)
	# (speedBrakeIncr) speed Brake increment per keystroke
	SpeedBrakeIncr	80	# (deg)
	Clda		0.048	# (Clda) roll moment from aileron offset
	Cldr		0.004	# (Cldr) roll moment from rudder offset
	Clp		-0.27	# (Clp) roll damping
	Cmq		-8.0	# (Cmq) pitch damping factor
	Cnr		-0.378	# (Cnr) yaw damping factor
	CmAlpha		-0.40	# (cmSlope) CmAlpha curve slope 
	CmFactor	-0.20	# (cmFactor) CmAlpha factor when stalled 
	MaxFuel		9750	# (maxFuel) maximum internal fuel (lb)
	# engine lag factor (how fast does it respond to throttle changes)
	EngineLag	-3.0
	# Engine data based on updated RD-33K engines cited in [AirI Aug89].
	# (maxThrust) max static thrust, military power (lb) 
	MaxThrust	27000
	# (maxABThrust) max static thrust, afterburner on  (lb) 
	MaxABThrust	44000

	Thrust	{		# (Thrust) Mach Number vs. thrust	
		0,	1,
		1.7,	1.5,
		2.0,	0.84,
		5,	0.5
		}
	ABThrust {		# (ABThrust) afterburner thrust table
		0,	1,
		0.5,	1,
		1,	1.21,
		1.7,	1.7,
		5,	1.64
		}
	# (spFuelConsump) specific fuel consump(lb fuel/lb T x hr)
	SpFuelConsump	0.68
	# (spABFuelConsump) AB specific fuel consump(lb fuel/lb T x hr)
	SpABFuelConsump	2.55
	# (groundingPoint) hypothetical single pt of contact w/ground 
	GroundingPoint	{ 0,  0,  6.5 }
	# (viewPoint) pilot's viewing location wrt CG
	ViewPoint	{ 14.75, 0,  -5.375 }

	# Landing Gear control parameters

	MuStatic	0.08	# (muStatic) static coeff of friction no-brakes 
	MuKinetic	0.05	# (muKinetic) moving coeff of friction no-brakes
	MuBStatic	0.7	# (muBStatic) static brakes-on
	MuBKinetic	0.6	# (muBKinetic) moving brakes-on

	MaxNWDef	72	# (maxNWDef) maximum nosewheel deflection (deg)
	NWIncr		0.0397	# (NWIncr) deflection for each unit (1.27/32)
	MaxNWS		85	# (maxNWS) maximum NWS velocity (fps)

	# (rm) location of main gear attachments
	Rm		{ -1.206000, 0.000000, 4.25 }
	# (rn) location of nose gear attachments
	Rn		{ 10.395000,  0.000000, 4.5 }
	Dm		10000	# main oleo damping factor
	Dn		1000	# nose oleo damping factor
	Km		105561	# main oleo spring factor
	Kn		23439.1	# nose oleo spring factor
	Gm		1.5	# main strut length with tire (ft)
	Gn		1.5	# nose strut length with tire (ft)
	CmMax		1.0	# (cmMax) main max oleo extension distance (ft)
	CnMax		0.75	# (cnMax) nose max oleo extension distance (ft)
	# (tailExtent) as we rotate, this part may drag 
	TailExtent	{ -18.165,  0.0,  1.191 }
	StructurePoints	15	# (structurePts) maximum structural damage 

	# Radar data based on N-019 Pulse Doppler radar cited in [AirI Aug89].

	RadarOutput	15000	# (radarOutput) radar output (watts)
	RadarTRange	38	# (radarTRange) tracking radar range (nm)
	RadarDRange	55	# (radarDRange) detection radar range (nm)
	TEWSThreshold	0	# Radar Warning Receiver threshold (watts)

	# Weapons

	WeaponCount	7

	HardPoint0	{ 7.0, -4.0, 0.0 }
	HardPoint1	{ 0.357, 15.6, 0.0 }
	HardPoint2	{ 0.357, -15.6, 0.0 }
	HardPoint3	{ 1.5, 9.0, 2.0 }
	HardPoint4	{ 1.5, -9.0, 2.0 }
	HardPoint5	{ 1.5, 8.0, 1.5 }
	HardPoint6	{ 1.5, -8.0, 1.5 }
	HardPoint7	{ 1.5, 10.0, 1.5 }
	HardPoint8	{ 1.5, -10.0, 1.5 }

	WeaponStation	0 "m61a1"	500	0	0
	WeaponStation	1 "aim9m"	0	0	0
	WeaponStation	2 "aim9m"	0	0	0
	WeaponStation	3 "aim9m"	0	0	0
	WeaponStation	4 "aim9m"	0	0	0
	WeaponStation	5 "aim9m"	0	0	0
	WeaponStation	6 "aim9m"	0	0	0

#COVER

	Object	"su30.obv"
	Description "Sukhoi Su-30 Multi-Role Fighter"

	DISEntityType	 1:2:222:2:9:0:0	# used Su-37 enumeration
	DISAltEntityType 1:2:225:1:3:3:0

	WingArea	600
	WingHalfSpan	24
	Chord		16
	EmptyWeight	50000
	MaxFuel		15000
	Ixx		5000
	Iyy		50000
	Izz		50000
	Rm		{-2.2325,  0,  8.53825}
	Rn		{24.1916,  0,  8.27663}
	Km		63456.8
	Kn		9791.8
	Gm		2
	Gn		2
	Dm		40000
	Dn		5000
	CmMax		1.0
	CnMax		1.5
	GroundingPoint	{0.0, 0.0, 11.9359}
	ViewPoint	{34.2729, 0, -8.89525}

	# (CDb) Drag Characteristic equation [Wave+body]
	# independent variable is mach number
	CDb	{		# (CDb) Drag Characteristic equation [Wave+body]
				# independent variable is mach number
		0.0,	0.020,
		0.2,	0.020,
		0.95,	0.015,
		1.05,	0.045,
		2.00,	0.030,
		10.0,	0.030
		}

	CLift	{		# (CLift) Lift-slope curve (vs alpha)
		-3.0,	0.0,
		-1.05,	0.0,
		-0.576,	-2.199,
		-0.556,	-2.23,
		-0.524, -2.199,
		0.524,	2.199,
		0.556,	2.23,
		0.576,	2.199,
		1.05,	0.0,
		2.0,	0.0
		}

	CnBeta	{		# (CnBeta) Yaw due to sideslip equation
		0,	-0.08125,
		0.523540, -0.078125,
		0.785340, -0.0609375,
		1.047198, 0.125,
		1.58,	0.0
		}

	ClBeta	{		# (ClBeta) Roll due to sideslip equation 
		0,	-0.0125,
		0.43633, -0.015,
		0.78540, 0.125,
		1.58,	0.0,
		3.142,	0.125,
		}

	MaxThrust	20000
	MaxABThrust	55000
	Thrust	{		# (Thrust) Mach Number vs. thrust	
		0,	1,
		1.7,	1.5,
		2.0,	0.84,
		5,	0.5
		}
	ABThrust {		# (ABThrust) afterburner thrust table
		0,	1,
		0.5,	1,
		1,	1.21,
		1.7,	1.7,
		5,	1.64
		}
	SpFuelConsump	0.7
	SpABFuelConsump	2.5
	EngineLag	-3

	Clda		0.048	# (Clda) roll moment from aileron offset
	Cldr		0.004	# (Cldr) roll moment from rudder offset
	Clp		-0.27	# (Clp) roll damping
	Cmq		-8.0	# (Cmq) pitch damping factor
	Cnr		-0.378	# (Cnr) yaw damping factor
	CmAlpha		-0.40	# (cmSlope) CmAlpha curve slope 
	CmFactor	-0.20	# (cmFactor) CmAlpha factor when stalled 

	# Radar data based on N-019 Pulse Doppler radar cited in [AirI Aug89].

	RadarOutput	15000	# (radarOutput) radar output (watts)
	RadarTRange	38	# (radarTRange) tracking radar range (nm)
	RadarDRange	55	# (radarDRange) detection radar range (nm)
	TEWSThreshold	0	# Radar Warning Receiver threshold (watts)

	StructurePoints	30	# (structurePts) maximum structural damage 

	# Weapons

	WeaponCount 7

	HardPoint0	{ 7.0, -4.0, 0.0 }
	HardPoint1	{ 0.357, 15.6, 0.0 }
	HardPoint2	{ 0.357, -15.6, 0.0 }
	HardPoint3	{ 1.5, 9.0, 2.0 }
	HardPoint4	{ 1.5, -9.0, 2.0 }
	HardPoint5	{ 1.5, 8.0, 1.5 }
	HardPoint6	{ 1.5, -8.0, 1.5 }
	HardPoint7	{ 1.5, 10.0, 1.5 }
	HardPoint8	{ 1.5, -10.0, 1.5 }

	WeaponStation	0 "m61a1"	500	0	0
	WeaponStation	1 "aim9m"	0	0	0
	WeaponStation	2 "aim9m"	0	0	0
	WeaponStation	3 "aim9m"	0	0	0
	WeaponStation	4 "aim9m"	0	0	0
	WeaponStation	5 "aim9m"	0	0	0
	WeaponStation	6 "aim9m"	0	0	0
	}


# F-16 C Falcon

aircraft "F-16" {

	Description "General Dynamics F-16C Fighting Falcon"
	Object		"f16.obv"
	WingArea	300.0	# (wingS) Wing surface area (ft^2)
	WingHalfSpan	16	# (wings) Wing half-span (ft)
	Chord		9.61	# (c) Mean geometric chord of wing (ft)
	AspectRatio	3.0	# (aspectRatio) aspect ratio
	EmptyWeight	14576	#(emptyWeight) Empty weight (lb)

	DISEntityType	 1:2:225:1:3:3:0
	DISAltEntityType 1:2:222:1:2:5:0

	# (I(x,y,z)) Moments of inertia
	Ixx		7240
	Iyy		49786
	Izz		54390

	# (cFlap) Lift due to flaps (yields Clift of 1.0 at max extension)
	CFlap		0.64279
	CLNegStall	17.0	# (deg)
	CLPosStall	30.0	# (deg)
	BetaStall	15.0	# (deg)

	CFlapDrag	0.0467	# (cFlapDrag) Drag due to Flaps
	CGearDrag	0.03	# (cGearDrag) Drag due to Gear
	CSpeedBrake	0.03	# (cSpeedBrake) Drag due to Speed Brake
				# at 90 degrees

	# (CDb) Drag Characteristic equation [Wave+body]
	# independent variable is mach number
	CDb	{		# (CDb) Drag Characteristic equation [Wave+body]
				# independent variable is mach number
		0.0,	0.020,
		0.2,	0.020,
		0.95,	0.015,
		1.05,	0.045,
		2.00,	0.030,
		10.0,	0.030
		}

	CLift	{		# (CLift) Lift-slope curve (vs alpha)
		-3.0,	0.0,
		-1.05,	0.0,
		-0.576,	-2.199,
		-0.556,	-2.23,
		-0.524, -2.199,
		0.524,	2.199,
		0.556,	2.23,
		0.576,	2.199,
		1.05,	0.0,
		2.0,	0.0
		}

	CnBeta	{		# (CnBeta) Yaw due to sideslip equation
		0,	-0.08125,
		0.523540, -0.078125,
		0.785340, -0.0609375,
		1.047198, 0.125,
		1.58,	0.0
		}

	ClBeta	{		# (ClBeta) Roll due to sideslip equation 
		0,	-0.0125,
		0.43633, -0.015,
		0.78540, 0.125,
		1.58,	0.0,
		3.142,	0.125,
		}

	CDBOrigin	0	# (CDBOrigin, CDBFactor) Drag due to sideslip
	CDBFactor	0.5	
	CDBPhase	0	# (CDBPhase) sideslip drag phase (deg)
	CYBeta		-1.14	# (CYbeta) Side-force from side-slip [dCY/dBeta]
	EffElevator	0.63	# (effElevator) Elevator effectiveness [Cmde(1/rad)]
	EffRudder	0.085	# (effRudder) Rudder effectiveness [CYdr(1/rad)]
	MaxRudder	20	# (maxRudder) max Rudder (deg)
	SeTrimTakeoff	0	# (SeTrimTakeoff) Elevator trim at takeoff (deg)
	MaxAileron	20	# (maxAileron) max Aileron (deg)
	MaxFlap		20	# (maxFlap) max flap setting (deg)
	# (flapRate) flap extension rate (about 2 secs to fully extend flaps)
	FlapRate	10	# (deg/sec)
	# (gearRate) gear extension rate (about 3 secs to fully extend gear)
	GearRate	30	# (deg/sec)
	MaxSpeedBrake	80	# (maxSpeedBrake) max Speed Brake setting (deg)
	# (speedBrakeRate) rate of speed brake extension (2 secs to full ext)
	SpeedBrakeRate	40	# (deg/sec)
	# (speedBrakeIncr) speed Brake increment per keystroke
	SpeedBrakeIncr	80	# (deg)
	Clda		0.048	# (Clda) roll moment from aileron offset
	Cldr		0.004	# (Cldr) roll moment from rudder offset
	Clp		-0.443	# (Clp) roll damping
	Cmq		-5.23	# (Cmq) pitch damping factor
	Cnr		-0.378	# (Cnr) yaw damping factor
	CmAlpha		-0.35	# (cmSlope) CmAlpha curve slope 
	CmFactor	-0.20	# (cmFactor) CmAlpha factor when stalled 
	MaxFuel		9750	# (maxFuel) maximum internal fuel (lb)
	# engine lag factor (how fast does it respond to throttle changes)
	EngineLag	-3.0
	# Engine data based on updated RD-33K engines cited in [AirI Aug89].
	# (maxThrust) max static thrust, military power (lb) 
	MaxThrust	14080
	# (maxABThrust) max static thrust, afterburner on  (lb) 
	MaxABThrust	23540
	Thrust	{		# (Thrust) Mach Number vs. thrust	
		0,	1,
		1.7,	1.5,
		2.0,	0.84,
		5,	0.5
		}
	ABThrust {		# (ABThrust) afterburner thrust table
		0,	1,
		0.5,	1,
		1,	1.21,
		1.7,	1.7,
		5,	1.64
		}
	# (spFuelConsump) specific fuel consump(lb fuel/lb T x hr)
	SpFuelConsump	0.68
	# (spABFuelConsump) AB specific fuel consump(lb fuel/lb T x hr)
	SpABFuelConsump	2.55
	# (groundingPoint) hypothetical single pt of contact w/ground 
	GroundingPoint	{ 0,  0,  6.5 }
	# (viewPoint) pilot's viewing location wrt CG
	ViewPoint	{ 15.58, 0, -2.71 }

	# Landing Gear control parameters

	MuStatic	0.08	# (muStatic) static coeff of friction no-brakes 
	MuKinetic	0.05	# (muKinetic) moving coeff of friction no-brakes
	MuBStatic	0.7	# (muBStatic) static brakes-on
	MuBKinetic	0.6	# (muBKinetic) moving brakes-on

	MaxNWDef	72	# (maxNWDef)maximum nosewheel deflection (deg)
	NWIncr		0.0397	# (NWIncr) deflection for each unit (1.27/32)
	MaxNWS		85	# (maxNWS) maximum NWS velocity (kts)

	# (rm) location of main gear attachments
	Rm		{ -1, 0, 4.5 }
	# (rn) location of nose gear attachments
	Rn		{ 14, 0, 4.5 }
	Dm		10000	# main oleo damping factor
	Dn		700	# nose oleo damping factor
	Km		45408.5	# main oleo spring factor
	Kn		3243.47	# nose oleo spring factor
	Gm		1.5	# main strut length with tire (ft)
	Gn		1.5	# nose strut length with tire (ft)
	CmMax		1.5	# (cmMax) main max oleo extension distance (ft)
	CnMax		1.5	# (cnMax) nose max oleo extension distance (ft)
	# (tailExtent) as we rotate, this part may drag 
	TailExtent	{ -18.165,  0.0,  1.191 }
	StructurePoints	15	# (structurePts) maximum structural damage 

	# Radar data based on N-019 Pulse Doppler radar cited in [AirI Aug89].

	RadarOutput	15000	# (radarOutput) radar output (watts)
	RadarTRange	60	# (radarTRange) tracking radar range (nm)
	RadarDRange	80	# (radarDRange) detection radar range (nm)
	TEWSThreshold	0	# Radar Warning Receiver threshold (watts)

	# Weapons

	WeaponCount	7

	HardPoint0	{ 7.0, -4.0, 0.0 }
	HardPoint1	{ 0.357, 15.6, 0.0 }
	HardPoint2	{ 0.357, -15.6, 0.0 }
	HardPoint3	{ 1.5, 9.0, 2.0 }
	HardPoint4	{ 1.5, -9.0, 2.0 }
	HardPoint5	{ 1.5, 8.0, 1.5 }
	HardPoint6	{ 1.5, -8.0, 1.5 }
	HardPoint7	{ 1.5, 10.0, 1.5 }
	HardPoint8	{ 1.5, -10.0, 1.5 }

	WeaponStation	0 "m61a1"	500	0	0
	WeaponStation	1 "aim9m"	0	0	0
	WeaponStation	2 "aim9m"	0	0	0
	WeaponStation	3 "aim9m"	0	0	0
	WeaponStation	4 "aim9m"	0	0	0
	WeaponStation	5 "aim9m"	0	0	0
	WeaponStation	6 "aim9m"	0	0	0


	}

# Cessna 172

aircraft "C-172" {

	Description "Cessna 172RG"
	Object		"c172.obv"
	WingArea	174.0	# (wingS) Wing surface area (ft^2)
	WingHalfSpan	16	# (wings) Wing half-span (ft)
	Chord		4.9	# (c) Mean geometric chord of wing (ft)
	AspectRatio	5.9	# (aspectRatio) aspect ratio
	EmptyWeight	1450	#(emptyWeight) Empty weight (lb)

	DISEntityType	 1:2:225:40:1:1:0 # T-41 trainer
	DISAltEntityType 1:2:225:40:1:1:0 # T-41 trainer

	# (I(x,y,z)) Moments of inertia
	Ixx		1000
	Iyy		7500
	Izz		8000

	# (cFlap) Lift due to flaps (yields Clift of 1.0 at max extension)
	CFlap		0.64279
	CLNegStall	14.0	# (deg)
	CLPosStall	17.0	# (deg)
	BetaStall	15.0	# (deg)

	CFlapDrag	0.0467	# (cFlapDrag) Drag due to Flaps
	CGearDrag	0.03	# (cGearDrag) Drag due to Gear
	CSpeedBrake	0.03	# (cSpeedBrake) Drag due to Speed Brake
				# at 90 degrees

	# (CDb) Drag Characteristic equation [Wave+body]
	# independent variable is mach number
	CDb	{		# (CDb) Drag Characteristic equation [Wave+body]
				# independent variable is mach number
		0.0,	0.020,
		0.2,	0.020,
		0.95,	0.015,
		1.05,	0.045,
		2.00,	0.030,
		10.0,	0.030
		}

	#  This is a hack: it assumes CLMax = 1.7 at 17 degrees

	CLift	{		# (CLift) Lift-slope curve (vs alpha)
		-3.0,	0.0,
		-1.05,	0.0,
		-0.3316, -1.65,
		-0.2967, -1.7,
		-0.2618, -1.65,
		0.2618,	1.65,
		0.2967,	1.7,
		0.3316,	1.65,
		1.05,	0.0,
		2.0,	0.0
		}

	CnBeta	{		# (CnBeta) Yaw due to sideslip equation
		0,	-0.08125,
		0.523540, -0.078125,
		0.785340, -0.0609375,
		1.047198, 0.125,
		1.58,	0.0
		}

	ClBeta	{		# (ClBeta) Roll due to sideslip equation 
		0,	-0.0125,
		0.43633, -0.015,
		0.78540, 0.125,
		1.58,	0.0,
		3.142,	0.125,
		}

	CDBOrigin	0	# (CDBOrigin, CDBFactor) Drag due to sideslip
	CDBFactor	0.5	
	CDBPhase	0	# (CDBPhase) sideslip drag phase (deg)
	CYBeta		-1.0	# (CYbeta) Side-force from side-slip [dCY/dBeta]
	EffElevator	0.45	# (effElevator) Elevator effectiveness
	EffRudder	0.35	# (effRudder) Rudder effectiveness
	MaxRudder	20	# (maxRudder) max Rudder (deg)
	SeTrimTakeoff	0	# (SeTrimTakeoff) Elevator trim at takeoff (deg)
	MaxAileron	20	# (maxAileron) max Aileron (deg)
	MaxFlap		40	# (maxFlap) max flap setting (deg)
	# (flapRate) flap extension rate (about 2 secs to fully extend flaps)
	FlapRate	6	# (deg/sec)
	# (gearRate) gear extension rate (about 3 secs to fully extend gear)
	GearRate	30	# (deg/sec)
	MaxSpeedBrake	80	# (maxSpeedBrake) max Speed Brake setting (deg)
	# (speedBrakeRate) rate of speed brake extension (2 secs to full ext)
	SpeedBrakeRate	40	# (deg/sec)
	# (speedBrakeIncr) speed Brake increment per keystroke
	SpeedBrakeIncr	0	# (deg)
	Clda		0.048	# (Clda) roll moment from aileron offset
	Cldr		0.004	# (Cldr) roll moment from rudder offset
	Clp		-0.27	# (Clp) roll damping
	Cmq		-8.0	# (Cmq) pitch damping factor
	Cnr		-1.0	# (Cnr) yaw damping factor
	CmAlpha		-0.30	# (cmSlope) CmAlpha curve slope 
	CmFactor	-0.20	# (cmFactor) CmAlpha factor when stalled 
	MaxFuel		240	# (maxFuel) maximum internal fuel (lb)
	# engine lag factor (how fast does it respond to throttle changes)
	EngineLag	-1.0
	# (maxThrust) max static thrust, military power (lb) 
	MaxThrust	400
	# (maxABThrust) max static thrust, afterburner on  (lb) 
	MaxABThrust	400
	Thrust	{		# (Thrust) Mach Number vs. thrust	
		0,	1,
		1.7,	1.5,
		2.0,	0.84,
		5,	0.5
		}
	ABThrust {		# (ABThrust) afterburner thrust table
		0,	1,
		0.5,	1,
		1,	1.21,
		1.7,	1.7,
		5,	1.64
		}
	# (spFuelConsump) specific fuel consump(lb fuel/lb T x hr)
	SpFuelConsump	0.1677
	# (spABFuelConsump) AB specific fuel consump(lb fuel/lb T x hr)
	SpABFuelConsump	0.1677
	# (groundingPoint) hypothetical single pt of contact w/ground 
	GroundingPoint	{ 0,  0,  3.35 }
	# (viewPoint) pilot's viewing location wrt CG
	ViewPoint	{ 0.2791, -0.7326, -1.7792 }

	# Landing Gear control parameters

	MuStatic	0.08	# (muStatic) static coeff of friction no-brakes 
	MuKinetic	0.05	# (muKinetic) moving coeff of friction no-brakes
	MuBStatic	0.7	# (muBStatic) static brakes-on
	MuBKinetic	0.6	# (muBKinetic) moving brakes-on

	MaxNWDef	30	# (maxNWDef) maximum nosewheel deflection (deg)
	NWIncr		0.0397	# (NWIncr) deflection for each unit
	MaxNWS		85	# (maxNWS) maximum NWS velocity (kts)

	# (rm) location of main gear attachments
	Rm		{ -0.3489, 4.0118, 2.0299 }
	# (rn) location of nose gear attachments
	Rn		{ 4.1165, 0.0, 2.029 }
	Dm		1000	# main oleo damping factor
	Dn		100	# nose oleo damping factor
	Km		5377	# main oleo spring factor
	Kn		547	# nose oleo spring factor
	Gm		1.0	# main strut length with tire (ft)
	Gn		1.0	# nose strut length with tire (ft)
	CmMax		0.5	# (cmMax) main max oleo extension distance (ft)
	CnMax		0.5	# (cnMax) nose max oleo extension distance (ft)
	# (tailExtent) as we rotate, this part may drag 
	TailExtent	{ -18.165,  0.0,  1.191 }
	StructurePoints	10	# (structurePts) maximum structural damage 

	# Radar data based on N-019 Pulse Doppler radar cited in [AirI Aug89].

	RadarOutput	0	# (radarOutput) radar output (watts)
	RadarTRange	0	# (radarTRange) tracking radar range (nm)
	RadarDRange	0	# (radarDRange) detection radar range (nm)
	TEWSThreshold	0	# Radar Warning Receiver threshold (watts)

	# Weapons

	WeaponCount	2

	HardPoint0	{ 7.0, -4.0, 0.0 }
	HardPoint1	{ 0.357, 15.6, 0.0 }
	HardPoint2	{ 0.357, -15.6, 0.0 }
	HardPoint3	{ 1.5, 9.0, 2.0 }
	HardPoint4	{ 1.5, -9.0, 2.0 }
	HardPoint5	{ 1.5, 8.0, 1.5 }
	HardPoint6	{ 1.5, -8.0, 1.5 }
	HardPoint7	{ 1.5, 10.0, 1.5 }
	HardPoint8	{ 1.5, -10.0, 1.5 }

	WeaponStation	0 "m61a1"	50	0	0
	WeaponStation	1 "aim9m"	0	0	0


	}