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|
# 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
}
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