[records]
1=Aircraft Name,text
1h=Test: "¯"±x²ß÷ø |¦ ×°
2=Description,text
3=Performance,text
4=Registration,text
100=Sim File Name,text
101=Normal Model File Name,text
103=Crash Model File Name,text
104=Panel File Name?,text
105=*Aircraft Type,int32
105h=0=Normal, 1=Helicopter, 2=Non-flyable(CFS AI Only)
300=*!Control KB Effectiveness,record
300h=Speeds for 1/2 and 1/8 Keyboard Control Increment
301=Fuselage,record
302=Fuel Tank Capacities,record
310=*Engine Type,int8
310h=0=Piston|1=Jet|2=Glider|3=Helicopter|4=Rocket|5=TurboProp
311=Number Of Engines,int16
312=Fuel Weight per Gallon,fwgt
313=*Reverse Thrust Throttle Percent,16pct
313h=Negative. Percent of throttle, not percent of thrust:-35 good for FS2K Turbines
314=Land Me,int16
315=Flaps Positions,int16
316=*Mmo Overspeed Warning (Mach),mach
316h=Maximum Operating Mach
317=Autopilot Settings,record
318=Flaps Available,BOOL
319=Aural Stall Warning,BOOL
320=*Control Surfaces,record
320h=Elevator, Aileron, Rudder, Flaps, Spoiler ..|Deflections affect related Sec 1101 parameters
322=Mixture Control Available,BOOL
323=Carb Heat Available,BOOL
324=Pitot Heater Available,BOOL
325=Gear Warning,record
327=Spoiler Available,BOOL
328=Taildragger,BOOL
329=Advanced Autopilot - Speed Hold Switches,record
330=*Propeller Type,int32
330h=1=Fixed|2=Auto Adjust|3=Manual Adjust
331=Strobe Lights Available,BOOL
332=Wheel Brakes Available,BOOL
333=OBS Availability,record
334=*Gyro Drift Available,BOOL
334h=Was 0=RMI/HSI 1=VOR/OBI
335=Avionics Availability,record
337=Spoiler Auto Deploy Available,BOOL
338=*Autobrake On,BOOL
338h=Turns Autobrake always On
339=Stick Shaker,record
340=Spoilerons,record
341=Elevators Effectivity,tbldb
342=Ailerons Effectivity,tbldb
343=Rudder Effectivity,tbldb
344=Smoke System Available,BOOL
400=*Wing Cl vs Relative Height - Ground Effect,tbldb
400h=X=Altitude(AGL)/Wingspan, Y=Cl Factor|Increase Y-1.0 by 20% to get sig. effect
401=*Wing Cl Factor vs Mach,tbldb
401h=1.0 at low Mach, Typ 1.22 near M=0.75|Drops rapidly past Cruise Mach|Affects Induced drag !
404=*Wing Cl vs AoA (rad),tbldb
404h=Cl[y], AoA (rad)[x] over full circle|AoA at max Cl determines stall|dCl/dAoA~2Pi*[AR/(1+AR)]*COS(Sweep)
;|Clmax typ 1.60*[AR/(1+AR)]*COS(Sweep)@0.271 (15.5 deg)|Cl=0 at ~-2.0 deg for cambered wings
410=*Mach Related?,tbl16
410h=Typ peaks near 64K at 0.2
411=*Mach Related * 65536?,tbl16
411h=Induced drag??
412=Mach Related,tbl16
413=Mach Related,tbl16
420=Elevator Effect vs Mach * 1024?,tbl16
421=Aileron Effect vs Mach * 1024?,tbl16
422=Rudder Effect vs Mach * 1024?,tbl16
423=Mach Related * 1024?,tbl16
430=*Mach Drag vs Mach * 2048,tbl16
430h=Typ peaks near 70-95 at M 1.0|Critical at Cruise Mach -set at M 0.8 & 1.0 to give correct value at Cruise|Reduce peak to reduce Mach 1 "wall"
433=*Pitching Moment vs Mach * 2048?,tbl16
433h=Typ peaks at 50 at Mach 1
440=?Zeros,Unknown
441=Mach Related,tbl16
442=?Zeros,Unknown
443=?Zeros,Unknown
450=?Zeros,Unknown
451=*Dihedral Effect Coeff vs Body AoA,tbldb
451h=Dihederal Effect Parameter (1101) factor vs Body AoA|Might set near zero or negative just past Stall AoA to model Spins
452=?Zeros,Unknown
453=Mach Related,tbl16
454=?Zeros,Unknown
455=Mach Related,tbl16
456=*!Roll Damping Coeff vs Body AoA,tbldb
456h=Might set near zero or negative just past Stall Body AoA to model Spins
460=*!WeatherVane Stability Coeff vs Body AoA,tbldb
460h=Might set to reduce WeatherVane Stability at stall|Was Pitch Damping Coefficient
459=?Zeros,Unknown
461=?Zeros,Unknown
462=Mach Related?,tbl16
463=?Zeros or Mach Related,Unknown
464=Yaw Damping Coeff vs Body AoA,tbldb
464h=
465=?Zeros,Unknown
473=*!Pitch Moment Coeff vs Body AoA (rad),tbldb
473h=Total Aircraft (not just Wing) Moment|Cm_a, dCm/DAoAb is about 1.0 in center|Inverted, due to Pitch Sign conv.
500=Engine FS98 Piston Engine (FS98/CFS AI),record
501=Engine FS98 Piston Torque vs RPM?,tbl16
503=*FS98 Prop,tbl16
503h=Efficiency? vs Blade Angle and J? (periodic in Beta or J)
504=*FS98 Prop,tbl16
504h=Thrust? vs Blade Angle and J? (periodic in Beta or J)
505=Engine CFS/FS2000 Piston Engine,record
506=*Engine Throttle Profile,tbldb
506h=Affects manifold pressure|Sets throttle Idle stop and max MP wrt intake
507=*Engine Torque vs Fuel/Air Mixture,tbldb
507h=Torque (normalized) vs Fuel/Air ratio|Can adjust SFC(0.45 HP/lb-hr is norm)|Do NOT edit past No. of Table Pairs
508=*Engine Torque Factor vs RPM,record
508h=Internal Torque/BMEP before friction torque ?|Set to get rated HP at Max RPM (59F, 29.92") after setting Friction HP|Values should be near constant above 1800 RPM|Induction system also reduces torque with inc RPM
509=*Engine[Per Cyl]/TurboProp Friction Torque vs RPM,tbldb
509h=Recip and TurboProp Shaft Friction Loss|Reciprocating Engines:| Friction HP per Cyl=RPM*Torque/5252| Total about 12% of BHP at 2400 RPM|Low end affects how fast prop stops|Speed and Torque may be relative in Turbines
510=*Propeller Parameters,record
510h=Power absorbed, P=Cp*rho*(n^3)*(d^5)|Torque, M=Ct*rho*(n^2)*(d^4)|P=2Pi*n*M; J=V/nd =TAS(mph)*88/RPM*d(ft); Eff=J*Ct/Cp|n=RPM/60; rho=air density (slugs/ft^3); d=Diameter (ft)
511=*Propeller Efficiency vs Blade Angle and Adv Ratio,tbl3d
511h=Table of Prop Efficiency Coefficients|Multiply entries by 0.92 to include typ Fuselage Interference Reduction
512=*Propeller Thrust Coefficient vs Blade Angle and Adv Ratio,tbl3d
512h=Table of Prop Thrust Coefficients|Sets engine loading at given Prop parameters
513=CFS/FS2000 Hydraulic (Elec?/Pneu?) Setup,record
514=*CFS/FS2000 Hydraulic (Elec/Pneu?) Output vs RPM,tbldb
514h=0.0 at RPM=0.0|Flattens at higher RPM
515=*!Aileron/Rudder Trim Variable Limit? (rad),record
515h=Aileron/Rudder Trim Variable|Similar to SEC 320 Pitch Trim Limit
516=*!Aileron/Rudder Trim Moment,record
516h=Trim Moments per radian deflection|Negative for Aileron, Positive for Rudder|Similar to SEC 1101 Pitch Trim
517=*!Elevator Moment Factor vs Dynamic Pressure (lb/ft^2),tbldb
517h=Models drop in effectivness with Dynamic Pressure, q|q=1/2 Density * V^2|Might be Neg near Mach 1
518=!Ailerons Moment Factor vs Dynamic Pressure (lb/ft^2),tbldb
519=!Rudder Moment Factor vs Dynamic Pressure (lb/ft^2),tbldb
520=CFS/FS2000 Rocket Engine,record
521=*!CFS/FS2000 Failure Level,record
521h=0.00: No Imparement to 1.000: Full Imparement|Any intermediate value may have same effect
522=*CFS/FS2000 Failure Level?,double
522h=0.00 to 1.00 (total failure) - Extra, C182=1.000
523=*CFS/FS2000 Gear Power Source,int32
523h=0=Electrical 1=Hydraulic, 2=Pneumatic, 3=Manual, 4=None|Extra=3
524=*CFS/FS2000 Flaps Power Source,int32
524h=0=Electrical 1=Hydraulic, 2=Pneumatic, 3=Manual, 4=None|Extra=4
525=!*Fuel CFS/FS2000 Left Main Tank,record
525h=Wing Tanks Add Roll MoI of 0.208 [0.186] * gallons * lateral_offset^2 per tank| JetFuel [Gasoline]|Vertical OS is normally negligible
526=Fuel CFS/FS2000 Right Main Tank,record
527=Fuel CFS/FS2000 Left Aux Tank,record
528=Fuel CFS/FS2000 Right Aux Tank,record
529=Fuel CFS/FS2000 Left Tip Tank,record
530=Fuel CFS/FS2000 Right Tip Tank,record
531=!*Fuel CFS/FS2000 Center 1 Tank,record
531h=Center Tanks add Pitch MoI of 0.208 [0.186] * gallons * longitudinal_offset^2 per tank| JetFuel [Gasoline]|Vertical OS is normally negligible
532=Fuel CFS/FS2000 Center 2 Tank,record
533=Fuel CFS/FS2000 Center 3 Tank,record
534=Fuel CFS2/FS2000 External 1 Tank,record
535=Fuel CFS2/FS2000 External 2 Tank,record
536=!CFS/FS2000 Elevator Moment Factor vs Body AoA,tbldb
537=!CFS/FS2000 Aileron Moment Factor vs Body AoA,tbldb
538=!CFS/FS2000 Rudder Moment Factor vs Body AoA,tbldb
539=*!CFS/FS2000 L Factor vs Body AoA,tbldb
539h=Pitch Related? Lift due to Elevator vs AoA?
540=Engine EGT,record
541=Engine CHT,record
542=Engine Radiator Water Temperature,record
543=Engine Oil Temperature,record
544=Engine Oil Pressure,record
545=Engine Fuel Pressure,record
546=*Roll Rate Factor vs G,tbldb
546h=X=G Level Y=Factor
600=Engine FS98 Jet,record
601=*Engine Jet Power Curve,tbl16
601h=May relate to power vs Mach|Changing can cause turbine surge at high speeds
602=*Engine Unknown,tbl16
602h=Thrust vs Mach??
603=Engine EPR,tbl16
604=Engine N1,tbl16
605=Engine Hydraulic Pressure,tbl16
606=Engine EGT,tbl16
1001=*!Moment of Inertia Values,record
1001h=Relative values are important|Iyy < Izz <= Iyy+Ixx|Ixz <= 0.02*Izz (Ixy~0.005*Izz might be good)
1002=*Engine (thrust) Locations,record
1002h=Set to Prop or near jet exhaust location
1003=Fuel Tank Locations (For Sec 302),record
1004=Landing Gear,record
1005=Scrape Points,record
1101=Primary Aerodynamics,record
1199=*Autopilot/Secondary Aerodynamics,record
1199h=May include autopilot gain constants|FS2K has 112 elements, FS98 and CFS|16 sect, 7 param ea?
1202=*!Yaw Damper,int32
1202h=Lower values limit rudder effect|Set to 4000+ for moderate damping in large AC|* Too high may cause climb in turns with Alt Hold *
1203=Autopilot Limits,record
1204=Main Wing,record
1205=*Horizontal Stabilizer,record
1205h=Most inoperative in FS2K -- Incidence has effect|Effects set in Sec 1101
1206=*Vertical Stabilizer,record
1206h=Most or all inoperative in FS2K|Effects set in Sec 1101
1300=Yet Another Name,text
1400=*Helicopter Vertical Stabilizer,record
1400h=Helicopter by Steve Baugh
1401=Helicopter Horizontal Stabilizer,record
1402=Helicopter Main Rotor,record
1403=Helicopter Tail Rotor,record
1404=Helicopter Fuselage Area and Drag,record
1500=CFS/FS2000 Unknown,record
;1500=CFS/FS2000 Unknown,int32
1501=*FS2000 Engine Turbine,record
1501h=SFC is constant at 0.50, 0.70 for Concorde Type airframe (5943)|Both values are too low
1502=*FS2000 Turbine CN1 vs CN2 and Mach No.,tbl3d
1502h=Corrected N1 vs Corrected N2 (top), Mach No. (left)|Corrected N1/N2 (vary with temp) relative to Gauge N1/N2
1503=*FS2000 Turbine LoMach CN2 vs Throttle and Pressure Ratio,tbl3d
1503h=Corrected N2 vs Throttle (%) (top), Atmosphere Pressure Ratio? (left) @ Low Mach No. (UL corner)|Pressure Ratio appears to be Pressure_SL/Pressure_at_Altitude 4.237 ~35,000 ft; 22.57 ~72,000 ft
1504=*FS2000 Turbine HiMach CN2 vs Throttle and Pressure Ratio,tbl3d
1504h=Corrected N2 vs Throttle (%) (top), Atmosphere Pressure Ratio? (left) @ High Mach No. (UL corner)|Pressure Ratio appears to be Pressure_SL/Pressure_at_Altitude 4.237 ~35,000 ft; 22.57 ~72,000 ft
1505=*FS2000 Turbine CN2? vs U,tbldb
1505h=U values change Corrected Fuel Flow but not PPH|Appears to affect N1/N2 coupling|Not in TurboProps (KingAir)
1506=*FS2000 Turbine Thrust Factor vs CN1 and Mach No.,tbl3d
1506h=Thrust Factor vs C?N1 (top), Mach No. (left)|Sets Thrust rel. to SL Static Thrust Ref
1507=*FS2000 Turbine Factor vs CN1? and Mach No.,tbl3d
1507h=May relate to N1 losses
1508=*FS2000 Turbine Turboprop U vs CN2?,tbldb
1508h=U values change Corrected Fuel Flow but not PPH|Appears to affect N1/N2 coupling and|Turboprop Torque. Not in Jets
1509=FS2000 Propeller Feathering,record
1510=FS2000 Propeller Synch Available,BOOL
1511=FS2000 Propeller Reversing,record
1512=FS2000 Vacuum System,record
1513=FS2000 !Unknown,record
1514=*FS2000 Turboprop Prop Torque (ft-lb),double
1514h=Use to set Continuous Rated SHP=(N2/Prop_Gear_Ratio)*Torque/5252|N2 normally 29920 so set:| Torque=SHP*Prop_Gear_Ratio*0.17553
1515=*!FS2000 Wing Planiform - MAC/CoG ect,record
1515h=Sets FS variables for CoG gauge, etc.|FS2K2: Sweep, Root Chord, Taper
1516=FS2000 Concorde Overspeed Table,BOOL
1517=*FS2000 Concorde Sounds?,BOOL
1517h=BOOL? 1 for Concorde, not in 777
1518=*Turboprop AC?,BOOL
1518h=C182, Sophwith=False, Mooney=N/R, KingAir=True
1519=*Advanced AC SW,BOOL
1519h=Extra=False, Mooney=N/R KingAir=True, MS747=True
1520=FS2000 Fuel System,record
1521=*FS2000 Turbine Reheat,BOOL
1521h=Concorde=True, 737-400=False
1522=FS2000 Turbine AC Switches,record
1523=*FS2000 Turbine Variable Intake Area,BOOL
1523h=Affects EPR reading, Max/Min(neg)Thrust|True for Concorde
1524=*FS2000 Turbine Reheat Thrust Factor vs Mach No.,tbldb
1524h=X=Mach No. Y=Thrust Factor with Afterburner
1525=*FS2000 Damping Coeff vs Dynamic Pressure? (lb/ft^2),tbldb
1525h=Damping Coeff? vs q?|Lear=0.00:1.0 - 1000.0:0.2
1526=*FS2000 Turbine ITT,record
1526h=Interstage Turbine Temperature Calib
1527=*FS2000 Unknown27,int32
1527h=Extra=0
1528=FS2000 Unknown28,record
1530=*FS2000 Unknown30,double
1530h=Props only? C182S=1.000
1531=*FS2000 Flaps True Deflection Factor vs Setting,record
1531h=Setting(linear)=N/No_Settings(Param315)|True_Defl=320:Flaps_Ang_Lt*1531:True_Defl_Fac
;Comment above out to enable tbldb form
1531=*FS2000 Flaps True Deflection Factor vs Setting,tbldb
1531h=X=Setting Factor, Y=True Deflection Factor
1532=*FS2000 Turbine EPR,record
1532h=Exhaust Pressure Ratio Calib
1533=FS2000 ?Flight Director Available?,BOOL
1534=!*FS2000 Wing Center of Lift Offset,record
1534h=Relative to Visual Model CoG
1535=!*CFS2 Control Factor 1 vs AoA,tbldb
1535h=Modifies Stability Derivative - Ignored in FS2K|Roll[Yaw?] Moment Factor?
1536=!*CFS2 Control Factor 2 vs AoA,tbldb
1536h=Yaw[Roll?] Moment Factor?
1537=!*CFS2 Yaw Moment vs Body AoA,tbldb
1537h=Adds small Yaw moment near stall AoA
1538=!*CFS2 Roll Moment vs Body AoA,tbldb
1538h=Adds small Roll moment near stall AoA
1539=!New,record
1540=!New,record
1541=!Pitch Derivatives,record
1542=!Roll? Derivatives?,record
1543=!Roll? Derivatives,record
1544=!New,record
1545=!Cl vs AoA,tbldb
1546=!Cm vs AoA,tbldb
1547=!New,record
1548=!*FS2K2 New,tbldb
1548h=C208[B]
;These data types are for the records only. Records with multiple
;data members are listed as record, and then must have their own entry
;under their record number. Unknown records should NOT be listed here.
;Valid types are...
;record, BOOL, int8, int16, int32, double, text, thrust, 16pct,
; /13.761
;ang16, aspd, mach, prpm, tbl16, tbldb, fwgt tbl3d and m256.
;i16/182, i32/10788? i32/5120 /256 /6.5[29]
;Entries for records with multiple data members.
;Number beginning with 1.
;Each entry has three comma delimited parts.
;First, the hex offset into the record (NOT the file offset) of the first byte of the data.
;Second, the data type as in [Data Types] above.
;If the type is unknown, this should have a hex number for the length in bytes of the data.
;Third, SHORT description. The text that goes next to the icon.
;You can include help text by using the entry number followed
;by the letter h. See below for some help text examples.
;Help text is displayed by right clicking the icon in the program.
;INI files can't have a return on a line in help text. Use "|".
;RAF: Placed "*" ahead of Parameters with Help below.
[300]
1=00,int16,Elevator - Speed for 1/2 KB Increment
2=02,int16,Elevator - Speed for 1/8 KB Increment
3=04,int16,Aileron - Speed for 1/2 KB Increment
4=06,int16,Aileron - Speed for 1/8 KB Increment
5=08,int16,Rudder - Speed for 1/2 KB Increment
6=0A,int16,Rudder - Speed for 1/8 KB Increment
[301]
1=00,m256,*Cockpit View Right+/Left- CoG (in)
1h=Pilot's view point from the center of the aircraft to one side|Ineffective in FS2K ?
2=02,m256,*Cockpit View Above+/Below- CoG (in)
2h=Pilot's view point from the center of gravity up.
3=04,m256,*Cockpit View Fore+/Aft- CoG (in)
3h=Pilot's view point from the center of gravity fore/aft.
4=06,int32,*CoG Height From Ground *1665 (in)
4h=Height for initial loading|Main Gear Length *1500 (Light AC) *1700 (Heavy AC)
5=0A,ang16,*Fuselage Angle
5h=Fuselage angle for initial loading|57.3*(Difference_in_Gear_Lengths/Distance_Center_to_Main_Gear)|Neg angle for Pos pitch on ground|Use ArcTan when Ratio is >0.25
[302]
1=00,int32,Fuel Tank Center (gallons)
2=04,int32,Fuel Tank Left Main (gallons)
3=08,int32,Fuel Tank Right Main (gallons)
4=0C,int32,Fuel Tank Left Aux (gallons)
5=10,int32,Fuel Tank Right Aux (gallons)
6=14,int32,Fuel Tank Left Tip (gallons)
7=18,int32,Fuel Tank Right Tip (gallons)
[317]
1=00,BOOL,Auto Pilot Available
2=04,BOOL,VS Hold Available
3=08,int16,*Unknown
3h=P51d=1000
4=0A,int16,VS Hold Default(fpm)
5=0C,BOOL,Autoland
[320]
1=00,double,Elevator Area - total (sq ft)
2=08,double,Aileron Area - total (sq ft)
3=10,double,Rudder Area (sq ft)
4=18,double,*Elevator Angle Up Limit (rad)
4h=All control surface limits affect max effect
5=20,double,Elevator Angle Down Limit (rad)
6=28,double,Aileron Angle Up Limit (rad)
7=30,double,Aileron Angle Down Limit (rad)
8=38,double,Rudder Angle Limit (rad)
9=40,double,*!Pitch Trim Variable Limit (rad)
9h=Sets Pitch Trim (Elevator Trim tab or H. Stab) Variable +/- limits|This also calibrates float8 Trim Variable
10=48,BOOL,Elevator Trim ON?
10h=Seems to have no effect in FS2K
11=4C,double,*unknown
11h=not an angle??
12=54,double,*unknown8
12h=Flaps chord/width related? No effect seen|0.40 for FS98 Bell Heli - Only parameter not 0.00
13=5C,double,*unknown9
13h=not an angle?
14=64,double,*Horiz Stab.a?
14h=30.0 in CFS|Larger in smaller AC
15=6C,double,*unknown10
15h=See *Unknown8|not an angle?
16=74,double,*Horiz Stab.b?
16h=-30.0 in CFS|Larger in smaller AC
17=7C,double,*Flaps Angle Limit (rad)
17h=Multiply 1101:"Lift(etc) Coeff - Flaps" by this to get Actual Maximum|0.7854 (45 deg) typ; 0.00 disables Flaps
18=84,double,*Spoilers Angle Limit (rad)
18h=Multiply 1101:"Drag(etc) Coeff - Spoilers" by this to get Actual Maximum|1.047 (60 deg) typ; 0.00 disables Spoilers
[325]
1=00,BOOL,Enable Gear Warning
2=04,int32,Horn Volume
3=08,double,*Alert - Flaps Angle (rad) - Gear Not Down
3h=Gear not down alert sounds if|landing gear is up at this flaps angle
4=10,double,*Alert - Flaps Angle (rad) - Closed Throttle
4h=Gear not down alert sounds if|landing gear is up at this flaps angle|with closed throttle
[329]
1=00,BOOL,Airspeed Hold Available
2=04,BOOL,Mach Hold Available
3=08,BOOL,*A/T Arm Switch (FS98:NOT) Available
3h=Reversed in FS98
[333]
1=00,BOOL,OBS1 Available
2=04,BOOL,OBS2 Available
[335]
1=00,BOOL,VOR 1 Available
2=04,BOOL,VOR 2 Available
3=08,BOOL,OMI Available
[339]
1=00,BOOL,Stick Shaker Available (FFB)
2=04,BOOL,Unknown2
[340]
1=00,BOOL,Spoilerons
2=04,double,Min (Max?) Flaps Angle (rad) for Spoilerons
3=0C,double,Min Ailerons Angle (rad) for Spoilerons
4=14,double,Aileron to Spoiler Gain
[341]
1=00,int32,No. of Table Pairs
2=04,double,Stick Movement A
3=0C,double,Elevator Response A
4=14,double,Stick Movement B
5=1C,double,Elevator Response B
6=24,double,Stick Movement C
7=2C,double,Elevator Response C
8=34,double,Stick Movement D
9=3C,double,Elevator Response D
10=44,double,Stick Movement E
11=4C,double,Elevator Response E
12=54,double,Stick Movement F
13=5C,double,Elevator Response F
14=64,double,Stick Movement G
15=6C,double,Elevator Response G
[342]
1=00,int32,No. of Table Pairs
2=04,double,Stick Movement A
3=0C,double,Aileron Response A
4=14,double,Stick Movement B
5=1C,double,Aileron Response B
6=24,double,Stick Movement C
7=2C,double,Aileron Response C
8=34,double,Stick Movement D
9=3C,double,Aileron Response D
10=44,double,Stick Movement E
11=4C,double,Aileron Response E
12=54,double,Stick Movement F
13=5C,double,Aileron Response F
14=64,double,Stick Movement G
15=6C,double,Aileron Response G
[343]
1=00,int32,No. of Table Pairs
2=04,double,Stick Movement A
3=0C,double,Rudder Response A
4=14,double,Stick Movement B
5=1C,double,Rudder Response B
6=24,double,Stick Movement C
7=2C,double,Rudder Response C
8=34,double,Stick Movement D
9=3C,double,Rudder Response D
10=44,double,Stick Movement E
11=4C,double,Rudder Response E
12=54,double,Stick Movement F
13=5C,double,Rudder Response F
14=64,double,Stick Movement G
15=6C,double,Rudder Response G
;Ground Effect
[400]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
.............
34=104,double,x17
35=10C,double,y17
;Lift Factor vs Mach
[401]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
.............
34=104,double,x17
35=10C,double,y17
[404]
1=00,int32,No. of Table Pairs
2=04,double,AoA 1
3=0C,double,CL 1
4=14,double,AoA 2
5=1C,double,CL 2
6=24,double,AoA 3
7=2C,double,CL 3
8=34,double,AoA 4
9=3C,double,CL 4
10=44,double,AoA 5
11=4C,double,CL 5
12=54,double,AoA 6
13=5C,double,CL 6
14=64,double,AoA 7
15=6C,double,CL 7
16=74,double,AoA 8
17=7C,double,CL 8
18=84,double,AoA 9
19=8C,double,CL 9
20=94,double,AoA 10
21=9C,double,CL 10
22=A4,double,AoA 11
23=AC,double,CL 11
24=B4,double,AoA 12
25=BC,double,CL 12
26=C4,double,AoA 13
27=CC,double,CL 13
28=D4,double,AoA 14
29=DC,double,CL 14
30=E4,double,AoA 15
31=EC,double,CL 15
32=F4,double,AoA 16
33=FC,double,CL 16
34=104,double,AoA 17
35=10C,double,CL 17
36=114,double,AoA 18
37=11C,double,CL 18
38=124,double,AoA 19
39=12C,double,CL 19
40=134,double,AoA 20
41=13C,double,CL 20
; ....
[410]
1=00,int16,v0
17=20,int16,v16
[411]
1=00,int16,v0
17=20,int16,v16
[412]
1=00,int16,v0
17=20,int16,v16
[413]
1=00,int16,v0
17=20,int16,v16
[420]
1=00,int16,Mach 0.0:
2=02,int16,Mach 0.2:
[421]
1=00,int16,v0
17=20,int16,v16
[422]
1=00,int16,v0
17=20,int16,v16
[423]
1=00,int16,v0
17=20,int16,v16
[430]
1=00,int16,Mach 0.0:
2=02,int16,Mach 0.2:
;Mach Pitching Momement
[433]
1=00,int16,Mach 0.0:
[451]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
[456]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
;.........
19=8C,double,y9
[460]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
;.........
18=8C,double,y9
[464]
1=00,int32,No. of Table Pairs
2=04,double,x1
3=0C,double,y1
;.........
19=8C,double,y9
[473]
1=00,int32,No. of Table Pairs
2=04,double,AoA 1
3=0C,double,CM 1
4=14,double,AoA 2
...............
42=154,double,AoA 21
43=15C,double,CM 21
; ....
[500]
1=0,int16,Gauge Oil Pressure Factor*3
2=2,int16,Gauge Oil Temp Factor*4096
3=4,int16,Gauge Oil Pressure Offset
4=6,int16,Gauge Oil Temp Offset
5=8,int16,Propeller Rate Factor *16384?
6=0A,int16,Propeller Scalar *16384?
7=0C,int16,Fixed Prop Factor
8=0E,prpm,Maximum Governed RPM
9=10,ang16,Propeller Pitch Max Flat
10=12,ang16,Propeller Pitch Min Full
11=14,int16,Minimum Governed RPM
12=16,int16,*Magneto Power Factor*1000
12h=May be *1024 but what does it do?|Affect RPM drop on one Magneto?
13=18,int16,Gauge Manifold Pressure Offset Factor * 1024
14=1A,int16,Gauge Manifold Pressure Scalar * 1024
15=1C,int16,Maximum Fuel Flow Scalar
16=1E,int16,Maximum Horsepower (CFS AI sets sound level)
17=20,int16,*!Specific Fuel Consumption * 256?
17h=Default is 138|138/256 = 0.539 lb/HP-hr|Rich SFC?
18=22,int16,*Propeller Diameter (in)
18h=See FS2000 Propeller Help
19=24,double,Prop Moment of Inertia (slug-ft^2)
20=2C,int16,*Gauge EGT Scalar*5120
20h=Factor may be 1.90512
21=2E,int16,*RPM Rate Scalar/Flywheel Effect
21h=May be just Flywheel Effect
22=30,int16,*Throttle Offset Factor *16384?
32h=0 to 1, typ 0.1024
23=32,int16,*Throttle Scalar *16384?
23h=0 to -1, typ -0.1024
24=34,int16,*Friction Torque Factor *64?
24h=Seems to have no effect
25=36,int16,Auto Set Factor
26=38,int16,Local RPM Scalar (AI Prop Animation)
27=3A,int16,Anti Ice Power
28=3C,int16,Prop Type
29=3E,int16,*Gauge Oil Pressure RPM Scalar (min)
29h=Oil Temp?|*35.0 for Max Oil Temp?
30=40,int16,*Gauge CHT Temp vs RPM? Scalar
30h=Adjusts CHT Reading|*17.5 for Max CHT?| Was "Oil Temp."
;31=42,int16,*unknown doesn't exist
;31h=Usually 0
[501]
;FS98 engine torque
1=00,int16,v0
;....
[503]
;FS98 engine/prop
1=00,int16,no 1
2=02,int16,no 2
.....
[504]
;FS98 engine/prop
1=00,int16,no 1
2=02,int16,no 2
.....
[505]
1=00,double,*Displacement per Cylinder (cu. in.)
1h=HP proportional to this
2=08,double,*Compression Ratio
2h=Higher CR increases HP slightly|6.0 to 9.0 typical
3=10,int32,*Number of Cylinders
3h=HP proportional to this
4=14,double,*RPM Max
4h=HP nearly proportional to this
5=1C,double,*Engine Power Sound Level? (HP)
5h=Sets sound level to HP developed?|Displacement, No. Cyls, Torque tables, etc. set HP
6=24,int32,Negative G Engine Effects (0=None 1=Cutoff 2=Partial)
7=28,int32,Engine Type (0=Air Cooled 1=Water Cooled)
8=2C,double,*!Relative Starter Torque
8h=Was propeller start Delay
9=34,BOOL,Turbo/Supercharged
10=38,double,Manifold Pressure Max (inHg)
11=40,double,*Manifold Pressure Min (inHg)
11h=Usually 1.0000 if Turbocharged|Affects Min RPM?
12=48,double,*Boost Gain
12h=Maximum MP/Ambient Air Pressure|Sets max speed/max altitude factor
13=50,double,*Critical Altitude
13h=Maximum altitude for full MP?|Seems to have no effect
14=58,int32,Emerg Boost Type (0=None 1=Water 2=Meth-Water 3=WEP)
15=5C,double,*Emergency Boost MP Offset (inHg)
15h=Change Rate
16=64,double,Emergency Boost MP Gain Offset Increase (inHg)
17=6C,BOOL,*AutoMixture
17h=FALSE=Manual Mixture - AutoMixture Available|TRUE=No Mixture Control - Locks AutoMixture on
18=70,BOOL,*AutoIgnition
18h=FALSE=Magneto Cutoff Available|TRUE=Magneto Cutoff Not Available:| Must use Fuel Cutoff to stop engine
[506]
1=00,int32,No. of Table Pairs
2=04,double,*Throttle Position 1
2h=Usually 0.0
3=0C,double,*Manifold Pressure Fact 1
3h=Adjusts Idle Speed - Typ 0.20
4=14,double,*Throttle Position 2
4h=Usually 1.0
5=1C,double,*Manifold Pressure Fact 2
5h=Adjusts WOT Flow Restriction - Typ 0.97
[507]
;CFS1 uses only three Pairs, FS2000/CFS2 use six
1=00,int32,No. of Table Pairs
2=04,double,Fuel/Air Ratio 1
3=0C,double,Torque Fact 1
4=14,double,Fuel/Air Ratio 2
5=1C,double,Torque Fact 2
6=24,double,Fuel/Air Ratio 3
7=2C,double,Torque Fact 3
8=34,double,*Fuel/Air Ratio 4
8h=Do not set in CFS!
9=3C,double,Torque Fact 4
10=44,double,*Fuel/Air Ratio 5
10h=Do not set in CFS!
11=4C,double,Torque Fact 5
12=54,double,*Fuel/Air Ratio 6
12h=Do not set in CFS!
13=5C,double,Torque Fact 6
[508]
1=00,int32,No. of Table Pairs
2=04,double,RPM 1
3=0C,double,Torque Fact 1
4=14,double,RPM 2
5=1C,double,Torque Fact 2
6=24,double,RPM 3
7=2C,double,Torque Fact 3
8=34,double,RPM 4
9=3C,double,Torque Fact 4
10=44,double,RPM 5
11=4C,double,Torque Fact 5
[509]
1=00,int32,No. of Table Pairs
2=04,double,RPM 1
3=0C,double,Torque 1 (ft-lb)
4=14,double,RPM 2
5=1C,double,Torque 2 (ft-lb)
6=24,double,RPM 3
7=2C,double,Torque 3 (ft-lb)
8=34,double,RPM 4
9=3C,double,Torque 4 (ft-lb)
[510]
1=00,BOOL,*!Prop Deice Available
1h=Untested
2=04,double,*!Prop Reference diameter (ft)
2h=To account for change in number of blades:| Same thrust: Dnew=Dold*(Nnew/Ncurrent)^1/4| 2 to 3 blades: (3/2)^1/4=1.1067| Same power: Dnew=Dold*(Nnew/Ncurrent)^1/5| 2 to 3 blades: (3/2)^1/5=1.085 (prev error fixed)
3=0C,double,*!!Prop MoI (slug-ft^2)
3h=MoI <=[~0.6](Prop_Weight(lb)[less hub]*Dia^2)/386 (was 1546)|Scales with Dia_Prop^5|Affects rate of RPM change and Gyro Effects:|Push Stick: Yaw to left and Pull to right
4=14,double,*Prop Pitch Max
4h=See "Fixed Pitch Blade Angle"
5=1C,double,Prop Pitch Min
6=24,double,*Governed RPM Min
6h=Minimum governed engine speed with CS props|Typ 1400 to 1800|Relative to N2=29920 for Turboprops
7=2C,double,*!Governer Rate?
7h=Appears to be 1/(10*Time_Constant)|Reduce to minimize 'surging' when Gov RPM is changed|FS2K=0.100 KingAir=0.004 CFS=0.01
8=34,double,*Engine Gear Ratio (to Prop)
8h=For Turboprop Gear Ratio=29920/Prop_RPM
9=3C,double,*Fixed Pitch Blade Angle
9h=For Sec 330 Prop Type "Fixed"; Typically measured at 0.75 radius
10=44,double,*!Low Speed Theory Limit (ft/sec)
10h=Prop thrust set by tables only after this speed|80.00 all known AC
[511]
;Prop Efficiency vs Blade Angle and Advance Ratio
;not needed with "3D Table" Type
1=00,int32,No. of columns
2=04,int32,No. of rows
3=08,double,Angle 0 deg
4=10,double,Eff at Adv Ratio 0.0
;............
[512]
;not needed with "3D Table" Type
;Prop Power/Thrust Factor vs Blade Angle and Advance Ratio
1=00,int32,No. of columns
2=04,int32,No. of rows
3=08,double,Angle 0 deg
4=10,double,Pwr Fact at Adv Ratio 0.0
;........
[513]
1=00,int32,*Number of Hydraulic Pumps or Aux Units?
1h=No of hydraulic pumps? (Elec/Pneu?)|Extra=0, other entries 0.0|but Sec 514 is same as CFS AC
2=04,double,*Scale Factor
2h=0.8000 in CFS and FS2K Turbine AC
3=0C,double,*Limit *144 (psi)
3h=Relative to 514-Output?, Normalization Factor?|998.000 in CFS|432000.00 (3000psi) in FS2K Turbine AC
4=14,double,*Rate of Change
4h=Appears to be 1/(10[0]*Time_Constant) 0.01000 in CFS and FS2K Turbine AC
5=1C,int32,*Elec/Hydr/Pneu? Switch
5h=May define type: Elec=0, Hydr=1, Pneu=2?, [Man=3?, None=4?]|Extra=0 Beech,P51d,737=1
6=20,int32,*Elec/Hydr/Pneu? Switch
6h=May define type: Elec=0, Hydr=1, Pneu=2?, [Man=3?, None=4?]|Extra,Beech,P51d,737=2
[514]
1=00,int32,No. of Table Pairs
2=04,double,Engine RPM 1
3=0C,double,Pressure 1 *144 (psi)
4=14,double,Engine RPM 2
5=1C,double,Pressure 2 *144 (psi)
6=24,double,Engine RPM 3
7=2C,double,Pressure 3 *144 (psi)
8=34,double,Engine RPM 4
9=3C,double,Pressure 4 *144 (psi)
10=44,double,*Engine RPM 5
10h=< 3000 RPM for piston, < 29992 RPM for turbine
11=4C,double,Pressure 5 *144 (psi)
[515]
1=00,double,*!Aileron
1h=Sets Aileron Trim Variable limit?
2=08,double,!Rudder
[516]
1=00,double,*!Aileron (neg)
1h=-0.05 to -0.1 is good for FS2000|0.0 for no Trim|Compare with Cl_da
2=08,double,*!Rudder (pos)
2h=0.2 is typical for FS2000, 0.03 for CFS|Compare with Cn_dr|May affect Autopilot Heading Hold
[520]
;CFS/FS2000 Rocket Engine
;1=00,double,Thrust (lb)
;2=08,double,*SFC? (1/sec)
;2h=lb/lb-sec
1=00,double,*!Specific Thrust Constant (lb-sec/gal)
1h=Thrust=STC * gal/sec
2=*!Fuel Flow Rate (gal/sec)
2h=Thrust Time=Capacity in gallons / Flow Rate
[521]
1=00,double,Unknown
2=08,double,*Hydraulics/Elec?
2h=Or, Landing Gear/Flaps
[525]
1=00,int32,*Fuel tank number
1h=Affects order of use?
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,*Unusable fuel
6h=May not function
7=2C,int32,Type (1=Internal/2=External)
[526]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[527]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[528]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[529]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[530]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[531]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[532]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[533]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[534]
1=00,int32,Fuel tank number
2=04,double,left/right offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[535]
1=00,int32,Fuel tank number
2=04,double,left/rightl offset (ft)
3=0c,double,up/down offset (ft)
4=14,double,forward/back offset (ft)
5=1c,double,capacity in gallons
6=24,double,Unusable fuel
7=2C,int32,Type (1=Internal/2=External)
[536]
1=00,int32,No. of Table Pairs
2=04,double,Ang 1
3=0C,double,Factor 1
4=14,double,Ang 2
5=1C,double,Factor 2
6=24,double,Ang 3
7=2C,double,Factor 3
8=34,double,Ang 4
9=3C,double,Factor 4
10=44,double,Ang 5
11=4C,double,Factor 5
[537]
1=00,int32,No. of Table Pairs
2=04,double,Ang 1
3=0C,double,Factor 1
4=14,double,Ang 2
5=1C,double,Factor 2
6=24,double,Ang 3
7=2C,double,Factor 3
8=34,double,Ang 4
9=3C,double,Factor 4
10=44,double,Ang 5
11=4C,double,Factor 5
[538]
1=00,int32,No. of Table Pairs
2=04,double,Ang 1
3=0C,double,Factor 1
4=14,double,Ang 2
5=1C,double,Factor 2
6=24,double,Ang 3
7=2C,double,Factor 3
8=34,double,Ang 4
9=3C,double,Factor 4
10=44,double,Ang 5
11=4C,double,Factor 5
[539]
1=00,int32,No. of Table Pairs
2=04,double,Ang 1
3=0C,double,Factor 1
4=14,double,Ang 2
5=1C,double,Factor 2
6=24,double,Ang 3
7=2C,double,Factor 3
8=34,double,Ang 4
9=3C,double,Factor 4
10=44,double,Ang 5
11=4C,double,Factor 5
[540]
1=00,double,EGT Scale Factor
2=08,double,*EGT Temp Limit (deg R)
2h=Subtract 460 for F
3=10,double,*EGT Rate of Change
3h=1/Time_Constant(sec)
[541]
1=00,double,CHT Scale Factor
2=08,double,*CHT Cooling Factor
2h=Effect of airflow
3=10,double,*CHT Temp Limit (deg R)
3h=Subtract 460 for F
4=18,double,*CHT Rate of Change
4h=1/Time_Constant(sec)
[542]
1=00,double,Water Temp Scale Factor
2=08,double,*Water Temp Cooling Factor
2h=Effect of airflow
3=10,double,*Water Temp Limit (deg R)
3h=Subtract 460 for F
4=18,double,*Water Temp Rate of Change
4h=1/Time_Constant(sec)
[543]
1=00,double,Oil Temp Scale Factor
2=08,double,*Oil Temp Cooling Factor
2h=Effect of airflow|Generally 0.0 for Turbines
3=10,double,*Oil Temp Limit (deg R)
3h=Subtract 460 for F
4=18,double,*Oil Temp Rate of Change
4h=1/Time_Constant(sec)|Default is often too fast - try 0.005 (200 sec)
[544]
1=00,double,Oil Pressure Scale Factor
2=08,double,Oil Pressure Limit * 144 (psi)
3=10,double,*Oil Pressure Rate of Change
3h=1/Time_Constant(sec)
[545]
1=00,double,Fuel Pressure Scale Factor
2=08,double,*Fuel Pressure Limit * 144 (psi)
2h=Varies with engine RPM
3=10,double,*Fuel Pressure Rate of Change
3h=1/Time_Constant(sec)
[546]
1=00,int32,No. of Table Pairs
2=04,double,G 1
3=0C,double,Factor 1
4=14,double,G 2
5=1C,double,Factor 2
6=24,double,G 3
7=2C,double,Factor 3
8=34,double,G 4
9=3C,double,Factor 4
10=44,double,G 5
11=4C,double,Factor 5
[600]
1=00,int32,Oil Pressure Factor (42 is 100%)
2=04,int32,*Oil Temp Factor (101.96 is 100%)
2h=was 101.12
3=08,int32,Oil Viscosity/Temp
4=0C,ang16,Thrust Vector (deg)
5=10,int32,*Peak Efficiency Altitude(ft)
5h=Fuel consumption seems to be minimum at this altitude
6=14,int32,*EGT Warm-up Time
6h=Power drops as EGT increases
7=18,int32,N1 Spool up time in msec due to Inertia
8=1C,int32,N2 Spool up time in msec due to Inertia
9=20,int32,*Fuel Consumption/TSFC
9h=Not Linear! May vary with cube|Turbofan default is 400 (SFC about 0.65)|Pure turbojets should be 440 or more (SFC about 1.1)
10=24,int32,Fuel Consumption Base
11=28,int32,Turbine Temp Base
12=2C,int32,Thrust Factor (32768 is 100%)
13=30,mach,*Mach Related
13h=Was 'Starter Speed RPM'
14=34,mach,*Mach Related
14h=Was 'Starter Cutout Speed RPM'
15=38,int32,*Speed Adjust RPM (for N1=100%)
15h=Can change this to limit max %N1 to spec
16=3C,int32,*Best Efficiency RPM (32768 is 100%)
16h=RPM for maximum efficiency|32768=100%|Might refer to N2 RPM
17=40,int32,*Flameout Altitude (meters)
17h=Default is 18,287 meters=60,000 ft
18=44,thrust,*Thrust Maximum Static S.L. (pounds per engine)
18h=Set for rated, not TO Thrust
19=48,int32,*Turbine Temp Gauge Factor (256 is 100%)
19h=Degrees C * 256
20=4C,int32,Turbine Temp Gauge Scalar (256 is 100%)
21=50,int32,*Compressor Factor (32768 is 100% ?)
21h=Little or no effect
[1001]
1=00,int32,*Ixx Moment of Inertia - Roll (slug-ft^2)
1h=See Sec 525 Help for add. Roll MoI due to wing tank fuel
2=04,int32,*Iyy Moment of Inertia - Pitch (slug-ft^2)
2h=See Sec 531 Help for add. Pitch MoI due to center tank fuel
3=08,int32,*Izz Moment of Inertia - Yaw (slug-ft^2)
3h=<= Ixx + Iyy for most AC
4=0C,int32,*Ixz Moment of Cross Inertia - Roll-Yaw (slug-ft^2)
4h=Yaw-Roll Inertial Coupling due to Acceleration in Roll/Yaw|Due to Vertical Fin above CoG|0<=Ixy<0.05Izz (Yaw)
[1002]
1=00,int32,Engine 1 Position Right+/Left- CoG (in)
2=04,int32,Engine 1 Position Above+/Below- CoG (in)
3=08,int32,Engine 1 Position Fore+/Aft- CoG (in)
4=0C,int32,Engine 2 Position Right+/Left- CoG (in)
5=10,int32,Engine 2 Position Above+/Below- CoG (in)
6=14,int32,Engine 2 Position Fore+/Aft- CoG (in)
7=18,int32,Engine 3 Position Right+/Left- CoG (in)
8=1C,int32,Engine 3 Position Above+/Below- CoG (in)
9=20,int32,Engine 3 Position Fore+/Aft- CoG (in)
10=24,int32,Engine 4 Position Right+/Left- CoG (in)
11=28,int32,Engine 4 Position Above+/Below- CoG (in)
12=2C,int32,Engine 4 Position Fore+/Aft- CoG (in)
[1003]
1=00,int32,Center Fuel Tank Position Right+/Left- CoG (in)
2=04,int32,Center Fuel Tank Position Above+/Below- CoG (in)
3=08,int32,Center Fuel Tank Position Fore+/Aft- CoG (in)
4=0C,int32,Main Fuel Tanks Position Lateral Offset CoG (in)
5=10,int32,Main Fuel Tanks Position Above+/Below- CoG (in)
6=14,int32,Main Fuel Tanks Position Fore+/Aft- CoG (in)
7=18,int32,Aux Fuel Tanks Position Lateral Offset CoG (in)
8=1C,int32,Aux Fuel Tanks Position Above+/Below- CoG (in)
9=20,int32,Aux Fuel Tanks Position Fore+/Aft- CoG (in)
10=24,int32,Tip Fuel Tanks Position Lateral Offset CoG (in)
11=28,int32,Tip Fuel Tanks Position Above+/Below- CoG (in)
12=2C,int32,Tip Fuel Tanks Position Fore+/Aft- CoG (in)
[1004]
1=00,int32,*!Type of Gear
1h=0=fixed|1=retractable|2=skids|3=skis[floats?]|4=floats[skis?]
2=04,BOOL,Steerable
3=08,int32,Main Gear Position Right+/Left- CoG (in)
4=0C,int32,Main Gear Position Above+/Below- CoG (in)
5=10,int32,*Main Gear Position Fore+/Aft- CoG (in)
5h=Typ -0.25 to -0.50 MAC behind CoL (50% to 75% MAC from Wing LE)
6=14,int32,Center Gear Position Right+/Left- CoG (in)
7=18,int32,Center Gear Position Above+/Below- CoG (in)
8=1C,int32,Center Gear Position Fore+/Aft- of CoG (in)
9=20,double,Cycle Time Nose/Tail
10=28,double,*Cycle Time Left Main
10h=This is often set a fraction of a second different from Right Main
11=30,double,Cycle Time Right Main
12=38,int32,*Main Gear Max Spring Load (lb)
12h=Set to 2.2 to 3.5 times empty weight load|This depends on Fore/Aft locations
13=3C,int32,*Main Gear Damping (lb per ft/sec?)
13h=Set to about 1/4 to 1/8 Max Main Load|Max_Load/Damping=2*Pi for Critical Damping?
14=40,int32,*Main Gear Crash Velocity *32768 ft/sec
14h=Typ 524288, 16 ft/sec
15=44,int32,*Center Gear Max Spring Load (lb)
15h=Set to approx. 0.6 to 1.0 of empty weight|This depends on Fore/Aft locations
16=48,int32,*Center Gear Damping (lb per ft/sec?)
16h=Set to about 1/4 to 1/8 Max Center Load
17=4C,int32,Center Gear Crash Velocity *32768 (ft/sec)
[1005]
1=00,int32,Fuselage Right+/Left- CoG (in)
2=04,int32,Fuselage Above+/Below- CoG (in)
3=08,int32,Fuselage Fore+/Aft- CoG (in)
4=0C,int32,Fuselage Crash Velocity *32768 (ft/sec)
5=10,int32,Tail Tip Offset CoG (in)
6=14,int32,Tail Tip Above+/Below- CoG (in)
7=18,int32,*Tail Tip Fore+/Aft- CoG (in)
7h=Set Tail so it doesn't sink below ground in spot view at high pitch
8=1C,int32,Tail Crash Velocity *32768 (ft/sec)
9=20,int32,*Wing Tip Offset CoG (in)
9h=Set Wing Tip so it doesn't sink below ground in spot view during roll
10=24,int32,Wing Tip Above+/Below- CoG (in)
11=28,int32,Wing Tip Fore+/Aft- CoG (in)
12=2C,int32,Wing Tip Crash Velocity *32768 (ft/sec)
13=30,int32,Aux1 Right+/Left- CoG (in)
14=34,int32,Aux1 Above+/Below- CoG (in)
15=38,int32,Aux1 Fore+/Aft- CoG (in)
16=3C,int32,Aux1 Crash Velocity *32768 (ft/sec)
17=40,int32,Aux2 Right+/Left- CoG (in)
18=44,int32,Aux2 Above+/Below- CoG (in)
19=48,int32,Aux2 Fore+/Aft- CoG (in)
20=4C,int32,Aux2 Crash Velocity *32768 (ft/sec)
[1101]
1=* --- Misc. ----- [10/29/01 Aired.ini Compiled by Ronald Freimuth]
1h=Much info from Forum at ||This file linked from URL
;
2=00,int16,*Airframe Type
2h=48=Cess|49=Gldr|50=Lear|51=Sop|52=Extra|53=737|310=B17|566=B24|822=B25|1078=109e|1334=109g|1590=110|1846=C47|2102=Do17|2358=Fw190|2614=He111|2870=Hurr|3126=Ju87|3382=Ju88|3638=Msquto|3894=P47|4150=P51|4406=P38|4662=Spit1|4918=Spit9|5174=Tmpst|5943=Concorde|more
;|5430=V1|more
3=02,int16,Stall Warning - Stick Shaker (kts)
4=04,aspd,*Vmo - Overspeed Warning (kts)
4h=Maximum Operating Indicated Airspeed (kts)
5=08,int16,*Gauge Airspeed Indicator Base (kts)
5h=Adds to the airspeed indication, often -10, |-5, -7 good for jets|Set so IAS is correct at cruise speeds|For AC which indicate IAS low at high AoA due|to Pitot Tube effects set next parameter to -10
6=0A,int16,*Airspeed Weight Factor * 32768?
6h=-29273[-30150 gives exact IAS at 120 kts] if Airspeed Base=-10; -32768 if Base=0
7=0C,double,Flaps Cycle Time (sec)
8=14,double,Spoiler Cycle Time (sec)
9=1C,int32,*Empty Weight (lb)
9h=Weight of aircraft without fuel|and payload (FS2000/CSF, if load is in AIRCRAFT.CFG)
10=20,ang16,*!Stall Warning - Body AoA@Clm (deg)
10h=Set at or before AoA at Clmax (Sec 404) - Wing AoI (Sec 1204)
11=22,ang16,*!AoA Related??
;11=22,int16,*x2
11h=P47D=3392/18.637deg?
12=24,int16,*x3
12h=P47D=3 - Small ang16 AoA??
13=26,int16,*Braking Strength - Max (ft/sec^2 * 2048?)
13h=May be in mph/sec^2 *2048|Defaults to -32768, max effort Flag|Otherwise 0 to 32767, More realistic values are 10,000-30,000|Max rate occurs only after full weight on tires
; 32767 is about 16 ft/sec^2:-0.5 G|May relate to Tire Coeff of Friction
14=* -------- G Limits --------
14h=Set to about 1.5X Rated Load Limits|(2808=3.00)
15=28,int16,Positive G Limit * 936
16=2A,int16,Negative G Limit * 936
17=2C,int16,Positive G Limit /w Flaps * 936
18=2E,int16,Negative G limit /w Flaps * 936
19=* -------- Drag ----------
19h=Divide by 2048 for actual values|Drag=Cd*q*S, q=(rho/2)*V^2|q~IASkt^2/520 (IASmph^2/391)
;Cf=Cdo*Wing_Area/Total_Wetted_Area: 0.004-0.011 typ
20=30,int16,*Cdo Drag Coefficient - Zero Lift * 2048
20h=Cdo=0.018-0.04 typ, based on Wing Area
21=32,int16,*Cd_df Drag Coefficient - Flaps * 2048
21h=Per Radian|Maximum Cdf = Cd_df * Max_Defl(rad) Sec 320
22=34,int16,*Cdg Drag Coefficient - Landing Gear * 2048
22h=Gear down. Not Per Radian
23=36,int16,*Cd_ds Drag Coefficient - Spoiler * 2048
23h=Per Radian|Maximum Cds = Cd_ds * Max_Defl(rad) Sec 320
24=38,18,* ----- Zeros (x4-x15) -----
24h=Not currently used:Check Hex view
25=50,ang16,*!Fuselage AoA at Min Induced Drag
25h=(AoAw@Cl=0) - (AoI+Twist/2) typ|Cd=Cdo + [(AoA+AoAmd)*(dCl/dAoA)Cl=0]^2 * Induced_Drag_Constant|dCl/dAoA is 'average Cl vs AoA slope' in TBL 404. Gritsevsky/Pierson
26=Spare
27= !* ------ 2048(16384) Scale Factor - Small (Large) Aircraft
27h=Two different scale factors appear to be used|2048 for Small (SEL), 16384 for Large (Multi Engine) AC|Probably set by 'Airframe Type'
28= * --- Stability Derivatives - Most are Per Radian -----
28h=_da,_de,_dr: 'due to' ailerons, elevator, rudder|Roll, Pitch, Yaw subcripts: Angles l,m,n; Rates p,q,r|Most normalised to qSc or qSb
29= --------- Lift ----------
30=52,int32,*!CL_adot Lift - AoA rate? *2048?
30h=Not effective in FS2K?|Mooney=2679, 777=6497|Merged with 1101:54
31=56,int32,*!CL_q Lift - Pitch rate? *2048?
31h=Affects 'bounce' in pitch|Mooney=-10134, 777=-17398, Lear=-55912|Merged with 1101:58
32=5A,int16,*CL_de Lift - Elevator *2048
32h=(MAC/Distance_Elevator) * Pitch_Moment-Elevator|Elevator and Horiz Stab Lift change load on Wing slightly when deflected
33=5C,int16,*CL_dh Lift - Horizontal Stabilizer *2048
33h=Negative, as Elevator for same Hstab sign convention|(MAC/Distance_Hstab) * Pitch_Moment-Hstab
34=5E,double,*CL_df Lift - Flaps
34h=Per radian|Maximum CLf = CL_df * Max_Defl(rad) Sec 320
35=66,double,*CL_ds Lift - Spoilers
35h=Per radian|Maximum CLs = CL_ds * Max_Defl(rad) Sec 320
36= --------- Roll --- +=Right Aileron Down -------
37=6E,int16,*Cl_beta Roll Moment - Sideslip (Dihedral) *2048
37h=0 for no roll back to level flight
38=70,int16,*!Cl_da Roll Moment - Ailerons (Control) *2048(16384)
38h=Aileron Control Factor|was 16384
39=72,int32,Cl_dr Roll Moment - Rudder *2048
40=76,int32,*!Cl_p Roll Moment - Roll Rate (Damping) *2048(16384)
40h=Typ 0.5 unscaled|was 16384
41=7A,int32,Cl_r Roll Moment - Yaw Rate *2048
42=7E,double,*Cl_?? - Sideslip??
42h=Pitch related?
43= --------- Pitch --- +=Nose Down -------
44=86,int32,*Cmo Pitch Moment Coeff at AoA=0 (Trim os) *2048
44h=Sets effective CoG, thus Trim|Affects Pitch Stability|+102 will add offset of 0.05 (equiv to -0.05 in NACA curves) to Wing Moment (TBL 473)|May adj for near zero trim in Cruise (+ moves nose down, Trim Up)|See H. Stab Incidence, Sec 1205
45=8A,int32,*Cm_adot Pitch Moment - AoA Rate?? *2048(16348?)
45h=Tendency to return to previous pitch|Was Pitch Moment - Pitch Slip Angle|Was 16348
46=8E,int32,*Cm_de Pitch Moment - Elevator (Control) *2048?
46h=Elevator Control Factor|(Distance_Elevator/MAC) * Lift-Elevator
47=92,int32,*Cm_dh Pitch Moment - Horizontal Stabilizer *2048
47h=Trim varies with this. See Sec 1205|If 'Lift - Horiz. Stab.' is neg. this should also be neg. (H. Stab Aft of Wing)|(Distance_Hstab/MAC) * Lift-Hstab
48=96,int32,*Cm_q Pitch Moment - Pitch Rate (Damping) *2048(16384)
48h=About 350,000 for large AC
49=9A,double,*Cm_dp Pitch Moment - Prop Effect
49h=Higher values help get tail up with prop wash
50=A2,double,*Pitch Elevator Response
50h=Affects Pitch Prop Effect, perhaps with speed
51=AA,double,*!Cm_dt Pitch Moment - Trim Range
51h=Total Pitch Moment Trim Range|Each 'click' of KB pitch trim is 1/1024 Range|See Sec 320 Trim Tab Limit|Affects Autopilot Altitude Hold. See SEC 1199 #14
52=B2,double,*Cm_df Pitch Moment - Flaps
52h=Per Radian|Maximum Cmf = Cm_df * Max_Defl(rad) Sec 320
53=BA,double,*Cmg Pitch Moment - Gear
53h=Gear down. Not Per Radian
54=C2,double,*Cm_ds Pitch Moment - Spoilers
54h=Per Radian|Maximum Cms = Cm_ds * Max_Defl(rad) Sec 320
55= --------- Yaw --- +=Nose Left -------
56=CA,int32,*Cn_beta Yaw Moment - Sideslip (Weathervane Stab) *2048
56h=Tendency to fly straight|Typ 300 in large AC
57=CE,int16,*Cn_p Yaw Moment - Roll Rate (Adverse) *2048
57h=Requires rudder during Roll to neutralize
58=D0,int32,*Cn_dr Yaw Moment - Rudder (Control) *2048
58h=Rudder Control Factor
59=D4,double,*Cn_dp Yaw Moment - Prop Effect
59h=Higher values increase rudder control from prop wash|Higher for tail draggers
60=DC,double,*Yaw Rudder Response
60h=Affects Yaw Prop Effect, perhaps with speed
61=E4,int32,*!Cn_da Yaw Moment - Aileron *2048?(16384?)
61h=Requires rudder to neutralize constant Aileron|Was Yaw ?Center of rotation|Was 16K,int16
62=E8,int16,*!Cn_r Yaw Moment - Yaw Rate (Damping) *2048(16384?)
62h=was 16384
63= --------- Side Forces --------------
64=EA,int32,*!CY_da Side Force - Aileron? *2048?
64h=Large values may add drag in slip|Was "Cn_da Yaw Moment-Aileron *2048?(16384?)" int16
65=EE,int16,CY_beta Side Force - Sideslip Angle *2048
66=F0,int16,*CY_dr Side Force - Rudder? *2048
66h=(b[span]/Distance_Rudder) * Yaw_Moment-Rudder?
67=F2,int32,CY_p Side Force - Roll Rate? *2048
68=F6,int32,CY_r Side Force - Yaw Rate (Skid) *2048
69= ---- Alternate Representations ------
[1199]
;Autopilot Loop Gains? FS98/CFS: 15 sets of 7; FS2K: 16 sets of 7
1=00,double,*1 HDG Hold Roll Rate?
1h=Affects ILS Lock and initial Aileron deflection|May set Roll Moment Limit|Approx. turn rate if not Bank Limited?: deg per 2 min turn?
2=08,double,*2 HDG Hold Gain??
2h=Affects LOC Lock
3=10,double,Unknown3 - HDG Rate FB ?[Lt]
4=18,double,4 HDG Rate FB ?[Lt]
5=20,double,HDG Rate FB?
6=28,double,Unknown6
7=30,double,Unknown7
8=38,double,*8 Aileron Related?
8h=Typ 1.70. Aileron Time Constant? HDG Rate FB?
9=40,double,Unknown9
10=48,double,10 ?ILS Rollout related?
;11=50,double,*11 HDG Tolerance
;11h=Too low adds jitter. Was 'Turn Rollout Angle(deg)'
11=50,double,*11 HDG Rollout Angle Related (deg)
11h=<0: 16+3/2 value; >0: 16+1/2 value (deg) [C. Lamb]
12=58,double,Unknown12
13=60,double,Unknown13
14=68,double,*!14 ALT Hold Gain?/Pitch Rate?
14h=Appears to be main adjustment if Trim/Elevator contol is changed|20.0 typical. Elev Defl?
Set 3
15=70,double,*15 ALT Hold Gain? - Rate [Lt]?
15h=Dec below 0.000060 to reduce jitter with AP|737-300=0.000028
16=78,double,Unknown16
17=80,double,17 ALT Rate FB??
18=88,double,*18 Vertical Speed Rate?
18h=1/(1000*TC)? Rate VS[I] changes|Reduce to <=0.0002 to smooth Alt Hold
19=90,double,Unknown19
20=98,double,20 AP Pitch Rate
21=A0,double,Unknown21
Set 4
22=A8,double,*22 ALT Rate FB?
22h=Increase above 68.0 to minimize overshoot at High VS settings?
23=B0,double,Unknown23
24=B8,double,Unknown24
25=C0,double,*!25 ALT Related
25h=Increase from 10.0 to 30.0+ helped at FL 350
26=C8,double,Unknown26
27=D0,double,*27 ALT Hold Tolerance?
27h=Normally 0
28=D8,double,Unknown28
Set 5
29=E0,double,29 NAV Lock Gain
30=E8,double,30 NAV Rate FB [Lt]?
31=F0,double,Unknown31
32=F8,double,*32 ILS Lock Gain
32h=0.4(small AC) -4(large AC)
33=100,double,*33 ILS Rate Lt?
33h=Larger Helped (15) (RAF)
34=108,double,Unknown34
35=110,double,*35 ILS Rate FB?
35h=Damping? (RAF)
Set 6
36=118,double,*Set6 CS Prop? Unknown36
36h=36 to 42 are 0.0 in jet, have values in C182|Prop Control?
37=120,double,Unknown37
38=128,double,Unknown38
39=130,double,Unknown39
40=138,double,Unknown40
41=140,double,Unknown41
42=148,double,Unknown42
Set 7
43=150,double,*43 GS Lock Gain/Offset
43h=Affects GS offset?
44=158,double,GS Rate Lt?
45=160,double,Unknown45
46=168,double,*46 GS Rate FB
46h=Typ 0.0008, inc may smooth GS autoland
47=170,double,Unknown47
48=178,double,*48 Landing smoothness
48h=Affects 'thump'. 3.5 may be good
49=180,double,Unknown49
Set 8
50=188,double,*!50 Pitch Rate FB?
50h=Affects ALT Hold Pitch Stability, Altitude hold in turns and Autoland| 25(small AC) to 670(large AC -not Concorde)
51=190,double,Unknown51
52=198,double,Unknown52
53=1A0,double,Unknown53
54=1A8,double,Unknown54
55=1B0,double,Unknown55
56=1B8,double,Unknown56
Set 9
57=1C0,double,Set9 Unknown57
58=1C8,double,Unknown58
59=1D0,double,Unknown59
60=1D8,double,Unknown60
61=1E0,double,Unknown61
62=1E8,double,Unknown62
63=1F0,double,Unknown63
Set 10
64=1F8,double,Set10 Unknown64
65=200,double,Unknown65
66=208,double,Unknown66
67=210,double,Unknown67
68=218,double,Unknown68
69=220,double,Unknown69
70=228,double,Unknown70
Set 11
71=230,double,Set11 Unknown71
72=238,double,Unknown72
73=240,double,Unknown73
74=248,double,Unknown74
75=250,double,Unknown75
76=258,double,Unknown76
77=260,double,Unknown77
Set 12
78=268,double,Set12 Unknown78
79=270,double,Unknown79
80=278,double,Unknown80
81=280,double,Unknown81
82=288,double,Unknown82
83=290,double,Unknown83
84=298,double,Unknown84
Set 13
85=2A0,double,*85 SPD Hold Gain
85h=0.6 tightens control - more Rate FB rqd
86=2A8,double,*86 SPD Hold Rate Lt?
86h=Rate Lt?, 0.001 may hold Mach/speed closer
87=2B0,double,*87 SPD Hold ??
87h=No effect seen
88=2B8,double,*88 SPD Hold Rate FB
88h=Damping - Adj for small or no overshoot|25 good for 737-300
89=2C0,double,*89 SPD Hold ??
89h=Said to affect SPD Hold 'plateau'
90=2C8,double,*90 SPD Hold ??
90h=Said to affect SPD Hold 'plateau'
91=2D0,double,*91 SPD "Feed Forward"
91h=Moves Throttle immediately when speed setting is changed|80 in 737-300
Set 14
92=2D8,double,Set14 Unknown92
93=2E0,double,Unknown93
94=2E8,double,Unknown94
95=2F0,double,Unknown95
96=2F8,double,Unknown96
97=300,double,Unknown97
98=308,double,Unknown98
Set 15
99=310,double,*Set15 99 TOGA Throttle Rate?
99h=Higher speeds throttle up, 2.50 norminal
100=318,double,Unknown100
101=320,double,Unknown101
102=328,double,*102 TOGA Rate FB?
102h=Higher slows throttle up, 10.0 normal
103=330,double,Unknown103
104=338,double,Unknown104
105=340,double,Unknown105
Set 16
106=348,double,*Set16 Unknown106
106h=FS2K+ only - Parameters are always the same|Don't seem to be required in FS2K - Can use FS98 SEC 1199
107=350,double,Unknown107
108=358,double,Unknown108
109=360,double,Unknown109
110=368,double,Unknown110
111=370,double,Unknown111
112=378,double,Unknown112
113= ---- All Section 1199 Preliminary -----
[1203]
1=00,double,*Bank Limit
1h=See 1199:1 - Turn Rate: Limits at low speeds
2=08,double,*Bank Limit - Max Flaps
2h=Interpolated for less than maximum Flaps|Often 10.00 or 20.00
3=10,double,*Autoland Throttle cut Alt?
3h=Often 120.00
4=18,double,*Autoland Flare Alt?
4h=Often 70.00
5=20,ang16,*Down Pitch Limit (pos)
5h=Typ 10 deg, set to avoid excessive descent rate
6=22,ang16,*Up Pitch Limit (neg)
6h=Typ 30 deg, set to avoid stall with Autopilot
[1204]
1=00,int32,*S Area (sq.ft)
1h=Reference for Lift (S*CL*q), Drags (S*Cd*q) and SideForces (S*CY*q)
2=04,int32,*b Span (in)
2h=Reference for Roll(Cl) and Yaw(Cn)? Moments|Moment=Cl*q*S*b; Cn*q*S*b ?
3=08,int32,*c Mean Aerodynamic Chord (in)
3h=Reference for Pitching(Cm) Moments|Moment=Cm*q*S*c|MAC~S*144/b (exact value may be higher)
4=0C,ang16,*Dihedral (deg)
4h=Inop in FS2K|Use 1101 'Dihedral' parameter
5=0E,ang16,*Incidence (deg)
5h=Angle of Wing Incidence|Typ 0.0 to 3.0 deg|Effective MAC Incidence = Incidence + Twist/2|Adjusts Pitch and Drag
6=10,ang16,*Twist (deg)
6h=Angle of Wing Twist|Typ 0.0 to -2.0 deg|Change in Pitch = Twist/2 - Incidence
7=12,int32,*Induced Drag Constant * 65536
7h=Cdi at Cl=1: 1/e*Pi*Aspect_Ratio|e=Efficiency factor:0.5 - 0.9|1101:50 must be set correctly
8=16,int32,*Center of Lift Fore+/Aft- of CoG (in)
8h=Inop in FS2K, See Sec 1101 "Pitch Moment Coeff"
9=1A,BOOL,*Winglets
9h=May reduce drag too much
[1205]
1=00,int32,Area (sq.ft)
2=04,int32,Span (in)
3=08,int32,*Longitudinal Position (in)
3h=Distance to 25% MAC? of Horiz Stab
4=0C,int32,*Efficiency Factor? * 8192?
4h=Accounts for fuselage interference with Horizontal Stab?|1.0 for "T" tail; 0.9 for normal
5=10,ang16,*!Incidence (deg)
5h=Positive creates Pitch up Moment with Neg 1101 "Lift-H.Stab" & "Pitch Moment-H.Stab"|This can be used to move Trim down
[1206]
1=00,int32,Area (sq.ft)
2=04,int32,!Vertical Position (in)
3=08,int32,*Longitudinal Position (in)
3h=Distance to 25% MAC? of Vertical Stab
4=0C,int32,*Efficiency Factor? * 8192?
4h=Accounts for fuselage interference with Vertical Stab?
[1400]
1=00,double,Vertical Stabilizer Surface Area (sq. ft.)
2=08,double,Vertical Stabilizer Span (ft.)
3=10,double,*Vertical Stabilizer Angle of Incidence (rad)
3h=Causes turn to left in cruise|Set to zero and adjust Lift Coefficient below
4=18,double,Vertical Stabilizer Position Fore/Aft (in.)
5=20,double,Unknown--Position Up/Down???
6=28,double,*Vertical Stabilizer Lift Coefficient
6h=Set AoI above to zero|and adjust this value for "hands off" in cruise.
7=30,double,Vertical Stabilizer Drag Coefficient
8=38,double,Vertical Stabilizer Efficiency
[1401]
1=00,double,Horizontal Stabilizer Area (sq. ft.)
2=08,double,Horizontal Stabilizer Span (ft.)
3=10,double,Horizontal Stabilizer Angle of Incidence (inop?)
4=18,double,Horizontal Stabilizer Position Fore/Aft (in.)
5=20,double,Unknown--Position Up/Down???
6=28,double,*Horizontal Stabilizer Lift Coefficient
6h=Adjust this value carefully for "hands off" in cruise.
7=30,double,Horizontal Stabilizer Drag Coefficient
8=38,double,Horizontal Stabilizer Efficiency
- Helicopter by Steve Baugh
[1402]
1=00,double,Main Rotor Position Right/Left CoG
2=08,double,Main Rotor Position Fore/Aft CoG
3=10,double,Main Rotor Position Above/Below CoG
4=18,double,*Main Rotor Thrust Vector Right/Left (rad)
4h=Causes roll and yaw at takeoff.|Also contributes to "crabbing" in cruise.
5=20,double,*Main Rotor Thrust Vector Fore/Aft (rad)
5h=Changes nose "dipping" on takeoff.|Also impacts pitch at cruise speeds.|Set to -1 to -4 degrees (1 deg = 0.01745 radian).
6=28,double,*Main Rotor Blade Length (ft. each)
6h=Adjust only slightly for change of rotor torque.|Impacts RPM and torque too much|for realistic values|16.625=default [116% torque @ SL]|15.85-->100%|16.1-->105%|16.35-->110%|16.85-->120%
7=30,double,*Main Rotor Blade Chord (ft.)
7h=Adjust this parameter to increase lift for heavier helos.
8=38,double,*Number of Main Rotor Blades
8h=Acts as multiplier for rotor lift.|Use rotor blade chord to adjust rotor lift.
9=40,double,*!!Main Rotor MOI
9h=MoI <=(RotorWeight(lb)*Dia^2)/386|Effects rate of RPM at startup/shutdown and autorotation.
10=48,double,*Main Rotor CLmin
10h=Rotor CL and thrust at minimum collective|Do not normally change!
11=50,double,*Main Rotor CLmax
11h=Rotor CL and thrust at maximum collective|Change (carefully!) for more powerful rotors.
12=58,double,*Main Rotor Drag Coefficient
12h=Do not normally change.
13=60,double,*Main Rotor Friction
13h=Do not normally change.
14=68,double,*Rotor Circle Surface Area
14h=Adjust for autorotation "glide" in proportion to helo's weight.
15=70,double,*Intake Area (sq.ft.)?
15h=No effect observed for non-zero values.
16=78,double,N2 Inertia (turbine)
16h=Impacts whole engine performance|Do not normally change.
[1403]
1=00,double,Tail Rotor Position Right/Left CoG
2=08,double,Tail Rotor Position Fore/Aft CoG
3=10,double,Tail Rotor Position Above/Below CoG
4=18,double,Unused?
5=20,double,Unused?
6=28,double,Tail Rotor Length (ft. total)
7=30,double,Tail Rotor Blade Chord (ft.)
8=38,double,Number of Tail Rotor Blades
9=40,double,*Tail Rotor MOI
9h=See Main Rotor MOI help
10=48,double,*Tail Rotor CLmin
10h=Do not normally change!|Causes spins in autorotation when fuel cut off.
11=50,double,*Tail Rotor CLmax
11h=Increase this value for increased cyclic authority|and control during spins.
12=58,double,Tail Rotor Drag Coefficient
13=60,double,Tail Rotor Friction
[1404]
1=00,double,Frontal Surface Area (sq. ft.)
2=08,double,Side Surface Area (sq. ft.)
3=10,double,Top Surface Area (sq. ft.)
4=18,double,Frontal Surface Drag Coefficient
5=20,double,Side Surface Drag Coefficient
6=28,double,Top Surface Drag Coefficient
[1500]
1=00,int16,Unknown1
2=02,int16,Unknown2
[1501]
1=00,double,*Thrust - Static SL Reference (lb)
1h=Set for Rated, Not TO Thrust|Modified by Factor in Table 1506|Less Afterburner
2=08,double,*Intake Throat Area (sq.ft)
2h=Larger values decrease Thrust at cruise Mach - higher Bypass Ratio|Concorde=16
3=10,double,*Spool Up Rate
3h=Appears to be 1/(100*Time_Constant) Affects N1/N2|Turboprop prop may slow rates - Dec Prop MoI if necessary
4=18,double,*Turbine N2 Max RPM Reference
4h=Internal N2 reference, not actual N2 RPM|TurboProp reduction gear on this shaft|See Parameter 1514
5=20,BOOL,Afterburner
6=24,double,*Bypass Ratio?
6h=Always 1.00 - no observed effect in FS2K|Bypass Ratio (N1 Pressure Ratio?) MS747=12.0
7=2C,double,*Relative Efficiency??
7h=Always 1.00 - no observed effect in FS2K|Relative to SFC=0.50/0.70?
;Turbine Table
[1505]
1=00,int32,No. of Table Pairs
2=04,double,U 1
3=0C,double,?CN2 1
4=14,double,U 2
5=1C,double,?CN2 2
................
20=94,double,U 10
21=9C,double,?CN2 10
[1509]
1=00,BOOL,Prop Feather Available
2=04,BOOL,Auto Feather Available
3=08,double,!*Min RPM for Feathering?
3h=Untested
4=10,double,Prop Feathered Blade Angle
5=18,double,*Feather delay?
5h=guess, typ 0.9
6=20,BOOL,!*Defeathering Accumulators?
6h=Untested (int32?)
[1511]
1=00,BOOL,Reverse Available
2=04,double,*!Idle Blade Angle
2h=Prop goes to this angle on gnd at Throttle=0%| Only if Reverse Available
3=0C,double,Reverse Blade Angle
[1512]
1=00,int32,*Independent Vacuum Pump
1h=Extra=0 Sopwith, Schweizer=3
2=04,int32,*Engine Driven Vacuum Pump
2h=Extra=1 Schweizer=0
3=08,double,*Vacuum Max for Gauges
3h=Failure if higher?
4=10,double,*Vacuum Rate of Change?
4h=Always 0.125? = 8 sec time constant
5=18,double,Vacuum Increase due to RPM
6=20,double,Vacuum at Idle
7=28,double,*Vacuum Min for Gauges
7h=Failure if lower?
8=30,int32,Emergency Vacuum Pump
9=34,double,Emergency Vacuum Suction
[1513]
1=00,double,*Unknown1
1h=MS747=1.000
2=08,double,*Unknown2
2h=MS747=0.000
[1515]
1=00,double,MAC Length (ft)
1h=13.17 MS-MD83
2=08,double,*MAC Leading Edge position (ft)
2h=Mean Aerodynamic Chord leading edge distance|from FS Reference_Position. Typ MAC/4
3=10,double,*Sweep - 1/4 Chord? (rad)
3h=0.0 in default AC|0.4276 (24.5deg) MS-MD83
4=18,double,*Chord - Root?
4h=Same as MAC or a little more in default AC|(when not 0.0) 23.10 MS-MD83
5=20,double,*Taper Ratio?
5h=0.0 or 1.0 in default AC|0.160 MS-MD83
[1520]
1=00,BOOL,*Fuel Injected
1h=Mooney, Extra=True, C182S=False
2=04,BOOL,Fuel Boost Pump
;FS2000 Turbine Engine Switches
[1522]
1=00,BOOL,*Unknown1
1h=Concorde=True, 777,737,Lear=True
2=04,BOOL,*Unknown2
2h=Concorde=True, 777,737,Lear=False
;was int32
[1525]
1=00,int32,No. of Table Pairs
2=04,double,*q 1
2h=0.000 lb/ft^2? typ
3=0C,double,*Factor 1
3h=1.000 typ
4=14,double,q 2
5=1C,double,Factor 2
6=24,double,q 3
7=2C,double,Factor 3
8=34,double,*q 4
8h=q 1000.0 lb/ft^2? typ
9=3C,double,*Factor 4
9h=0.200 typ
;FS2000 Turbine ITT
[1526]
1=00,double,ITT Scale Factor
2=08,double,*ITT Limit (deg R)
2h=Subtract 460 for F|2400.0 gives 700 C in King Air
3=10,double,ITT *Rate of Change
3h=1/Time_Constant(sec)
;FS2000 Props
[1528]
1=00,double,*Unknown1
1h=Extra all=1.00, Not in Mooney
2=08,double,Unknown2
3=10,double,Unknown3
4=18,double,Unknown4
[1531]
1=00,int32,No. of Table Pairs
2=04,double,Setting 1
3=0C,double,True Deflection Factor 1
4=14,double,Setting 2
5=1C,double,True Deflection Factor 2
6=24,double,Setting 3
7=2C,double,True Deflection Factor 3
8=34,double,*Setting 4
8h=Factors 4+ may not be available
9=3C,double,True Deflection Factor 4
10=44,double,Setting 5
11=4C,double,True Deflection Factor 5
;FS2000 EPR, only some jets
[1532]
1=00,double,*EPR Scale Factor
1h=Appears to have no effect
2=08,double,*EPR Calibrate
2h=Might set for correct value at rated SSL thrust, AC Braked|Typ 1.40
3=10,double,EPR Rate of Change?
[1534]
1=00,double,CoL Offset Right+/Left- (ft)
2=08,double,CoL Offset Up+/Down- (ft)
3=10,double,*CoL Offset Fore+/Aft- (ft)
3h=Center of Lift relative to Visual Model|-63.00 in Concorde
[1539]
1=00,double,Ukn1
2=08,double,Ukn2
3=10,double,Ukn3
4=18,double,Ukn4
5=20,double,Ukn5
6=28,double,Ukn6
[1540]
1=00,double,Ukn1
2=08,double,Ukn2
3=10,double,Ukn3
4=18,double,Ukn4
[1541]
1=00,double,Cm_de?
2=08,double,CL_de?
3=10,double,Ukn3
4=18,double,CL_q?
5=20,double,CL_adot?
6=28,double,Cm_adot?
7=30,double,Cm_q?
8=38,double,Ukn8
9=40,double,CD_de??
10=48,double,Ukn10
11=50,double,Cm_a?
12=58,double,Ukn12
13=60,double,Ukn13
[1542]
1=00,double,Cl_p??
2=08,double,Ukn2
3=10,double,Ukn3
4=18,double,Cl_da??
[1543]
1=00,double,Cl_??
2=08,double,Ukn2
3=10,double,Cl_p?
4=18,double,Cl_da?
5=20,double,Cl_beta?
6=28,double,Cl_beta?
[1544]
1=00,double,Ukn1
2=08,double,Ukn2
3=10,double,Ukn3
4=18,double,Ukn4
5=20,double,Ukn5
6=28,double,Ukn6
7=30,double,Ukn7
8=38,double,Ukn8
9=40,double,Ukn9
;[1545] tbldb
;1=00,double,Ukn1
;[1546]
;1=00,double,Ukn1
[1547]
1=00,double,Ukn1
2=08,double,Ukn2
3=10,double,Ukn3
End