# 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)
	WingHeight  2.4     # (wingh) Height of the wing aerodyn. center above CM (ft)
	Chord       4.9 # (c) Mean geometric chord of wing (ft)
	AspectRatio 5.9 # (aspectRatio) aspect ratio
	EmptyWeight 1450    #(emptyWeight) Empty weight (well, actually mass) (lb)

	# Max. wing load:
	MaxLoadZPositive    10070  # 3.8*MTOW (+3.8 g)
	MaxLoadZNegative    3975  # 1.5*MTOW (-1.5 g)

	DISEntityType    1:2:225:40:1:1:0
	DISAltEntityType 1:2:225:40:1:1:0

	# (I(x,y,z)) Moments of inertia (lb ft^2)
	Ixx     1000
	Iyy     7500
	Izz     8000

	# (cFlap) Lift due to flaps (yields Clift of 1.0 at max extension)
	CFlap       1.47
	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,    0.034,
		0.2,    0.034,
		0.95,   0.020,
		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,
		-0.3316, -1.65,
		-0.2967, -1.7,
		-0.2618, -1.65,
		0.2618, 1.65,  # 15 DEG  (CLmax, stall begin)
		0.2967, 1.2,   # 17 DEG
		0.3316, 0.8,   # 19 DEG
		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 1.00    # (effElevator) Elevator effectiveness
	EffRudder   0.50    # (effRudder) Rudder effectiveness
	MaxRudder   20  # (maxRudder) max Rudder (deg)
	MaxAileron  20  # (maxAileron) max Aileron (deg)
	MaxFlap     30  # (maxFlap) max flap setting (deg)
	# (flapRate) flap extension rate (about 2 secs to fully extend flaps)
	FlapRate    3   # (deg/sec)
	# (gearRate) gear extension rate (about 3 secs to fully extend gear)
	GearRate    15  # (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

	EngineType "GenericPistonEngine"
	MaxFuel     240 # (maxFuel) maximum internal fuel (lb)
	# engine lag factor (how fast does it respond to throttle changes)
	EngineLag   -2.0
	# (maxThrust) max static thrust, military power (lbf) 
	MaxThrust   500
	# (maxABThrust) max static thrust, afterburner on  (lbf) 
	MaxABThrust 500
	Thrust  {       # (Thrust) Mach Number vs. thrust   
		0,  1,
		0.1, 0.95,
		0.2, 0.90,
		1.7,    0.5,
		5,  0.5
		}
	ABThrust {      # (ABThrust) afterburner thrust table
		0,  1,
		1.7,    1.5,
		2.0,    0.84,
		5,  0.5
		}

	HasThrustReverser 0  # (hasThrustReverser) 0=no, otherwise yes
	# (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
	# (viewPoint) pilot's viewing location wrt CM
	ViewPoint   { 0.2791, -0.7326, -1.7792 }

	# Landing Gear control parameters

	MuStatic    0.03    # (muStatic) static coeff of friction no-brakes 
	MuKinetic   0.02    # (muKinetic) moving coeff of friction no-brakes
	MuBStatic   0.6 # (muBStatic) static brakes-on
	MuBKinetic  0.5 # (muBKinetic) moving brakes-on

	MaxNWDef    30  # (maxNWDef) maximum nosewheel deflection (deg)

	# (rm) location of right main gear attachments
	Rm      { -1.3, 4.25, 2 }
	# (rn) location of nose gear attachments
	Rn      { 3.9, 0, 1.9 }
	Dm      300     # main oleo damping factor (lbf s/ft)
	Dn      600     # nose oleo damping factor (lbf s/ft)
	Km      9200    # main oleo spring factor (lbf/ft)
	Kn      5400    # nose oleo spring factor (lbf/ft)
	Gm      0.7 # 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 }

	# Speed limits at MTOW. Leave undefined or set to 0 if unknown.
	MTOW   2650.0    # maximum takeoff weight (lb)
	#Vs0     42.0    # stall speed, full flaps (KIAS)
	#Vs1     50.0    # stall speed, no flaps (KIAS)
	Vfe    100.0    # max speed with flaps extended (KIAS)
	Vno    145.0    # normal operation speed (KIAS)
	Vne    164.0    # never exceed speed (KIAS)

	StructurePoints 1  # (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 0
}