CFS2 Configuration file
The Aircraft CFG FILE

[FLIGHT_TUNING] Section

The [FLIGHT_TUNING] section contains parameters that define the aerodynamic performance, stability, flight control and trim effectiveness of your aircraft.

Here is the [FLIGHT_TUNING] section from Flerk's Corsair with comments removed ...

[FLIGHT_TUNING]
cruise_lift_scalar = 1.0
parasite_drag_scalar = 1.0
induced_drag_scalar = 1.0
elevator_effectiveness = 1.0
aileron_effectiveness = 1.0
rudder_effectiveness = 1.0
pitch_stability = 1.0
roll_stability = 1.0
yaw_stability = 1.0
elevator_trim_effectiveness = 1.0
aileron_trim_effectiveness = 1.0
rudder_trim_effectiveness = 1.0

NOTE
The values for each of the [FLIGHT_TUNING] parameters act as multipliers on the default parameter values specified in the AIR file for your model. For example, a value of 1.1 increases the default value by 10%. A value of 0.9 decreases the default value by 10%.

If no value is set for a [FLIGHT_TUNING] parameter, CFS2 defaults to a value of 1.0.

Aerodynamic Parameters
cruise_lift_scalar = 1.0
parasite_drag_scalar = 1.0
induced_drag_scalar = 1.0

cruise_lift_scalar = 1.0

CL0 is a multiplier for the wing's coefficient of lift at zero angle of attack. In this context, "cruise lift" refers to the wing operating at the relatively small angles of attack which are typical for an airplane in cruise flight.

This scaling is decreased linearly as angle of attack moves toward the critical (stall) angle of attack, which prevents destabilizing low speed and stall characteristics at high angles of attack. Modify this value to set the angle of attack (and thus pitch) for a cruise condition. A negative value is not advised, as this will result in extremely unnatural flight characteristics.

parasite_drag_scalar = 1.0

Cd0 is a multiplier for the aircraft's total parasite drag. Drag is the aerodynamic force that acts to impede an aircraft's movement through the air. Parasite drag is composed of form drag, which results from the physical shape of the aircraft interrupting streamlined airflow, and skin friction, which is the result of every rivet head, antenna, antenna wire or other protuberance on the aircraft that sticks into the airstream.

A negative value is not advised, as extremely unnatural flight characteristics will result.

induced_drag_scalar induced_drag_scalar = 1.0

Cdi is a multiplier for the aircraft's total induced drag. Induced drag is the byproduct of the wing producing lift and it increases as the wing's angle of attack increases.

A negative value is not advised, as extremely unnatural flight characteristics will result.

Flight Control Effectiveness Parameters
elevator_effectiveness = 1.0
aileron_effectiveness = 1.0
rudder_effectiveness = 1.0
elevator_trim_effectiveness = 1.0
aileron_trim_effectiveness = 1.0
rudder_trim_effectiveness = 1.0

elevator_effectiveness = 1.0

Cmde is a multiplier for the aircraft's elevator effectiveness.

A negative value reverses the normal effect of the control.

aileron_effectiveness = 1.0

Clda is a multiplier for the aircraft's elevator effectiveness.

A negative value reverses the normal effect of the control.

elevator_trim_effectiveness = 1.0

Cmdetr is a multiplier for the aircraft's elevator trim effectiveness.

A negative value reverses the normal effect of the control.

aileron_trim_effectiveness = 1.0

Cldatr is a multiplier for the aircraft's aileron trim effectiveness.

A negative value reverses the normal effect of the control.

rudder_trim_effectiveness = 1.0

Cndrtr is a multiplier for the aircraft's rudder trim effectiveness.

A negative value reverses the normal effect of the control.

Stability Parameters

A properly trimmed airplane is an inherently stable vehicle in flight ... it will fly straight and level just fine all by itself. If it is disturbed about the pitch, roll or yaw axis by wind gusts or pilot input, positive damping forces will return it to its original trimmed flight condition. This explains why you have to use control force to hold the aircraft in a turn. If you let off on the controls, the aircraft will gradually level itself.

A helicopter however, is not inherently stable. If left to itself, it will seek the shortest route to earth. If it is disturbed about the pitch, roll or yaw axis by wind gusts or pilot input, negative damping forces cause it to diverge away from its original flight condition. This is why the helicopter pilot must always have his hands on the controls and why control forces are light. You are not trying to overcome the inherent stability of the aircraft ... there is none.

pitch_stability = 1.0
roll_stability = 1.0
yaw_stability = 1.0

pitch_stability = 1.0

Cmq is a multiplier for the aircraft's pitch stability.

A negative value results in an unstable characteristic about the pitch (X) axis.

roll_stability = 1.0

Clp is a multiplier for the aircraft's roll stability.

A negative value results in an unstable characteristic about the roll (Z) axis.

yaw_stability = 1.0

Cnr is a multiplier for the aircraft's yaw stability.

A negative value results in an unstable characteristic about the yaw (Y) axis.

[FLAPS.n] Section

The parameters in this section let you configure and adjust the way your aircraft's wing flaps operate in flight.

Here is the [FLAPS.0] section from Flerk's Corsair with comments removed ...

[FLAPS.0]
type=1
span-outboard=0.125
extending-time=5.0
flaps-position.0=0, 0
flaps-position.1=16
flaps-position.2=32
flaps-position.3=48
flaps-position.4=64
flaps-position.5=80
damaging-speed=201
blowout-speed=305

[flaps.0]

flap_number This parameter defines the index for this flap set. If your aircraft uses only trailing edge flaps, the entire flap set is defined under [flaps.0]. If there are both leading and trailing edge flaps, one set is defined under [flaps.0], the other under [flaps.1].

type = 1

This parameter sets the type of flap used on this aircraft.

   1 = Trailing edge flaps
   2 = Leading edge flaps

span-outboard = 0.125

This parameter defines the width of the flaps as a percentage of the wing semi-span (width of one wing). Values range from 0.0 to 1.0.

extending-time = 5.0

This parameter defines the width of the flaps as a percentage of the wing semi-span (width of one wing). Values range from 0.0 to 1.0.

flaps-position.0 = 0, 0

This parameter indexes each discrete flap position available in your aircraft's flap settings. Position ".0" always refers to the fully retracted setting. Subsequent positions are numbered in consecutive order from fully retracted to fully extended.

flaps-position.0 = 0, 0

flap_extension, flap_inhibit_speedThe flap extension parameter defines the displacement angle of the flaps in degrees. The flap inhibit speed defines the indicated airspeed in knots above which flap movement may be inhibited. If flap inhibit speed is omitted or set to zero, flap movement is unlimited. Flap movement is scaled by Realism settings when aircraft is flown above the flap inhibit airspeed.

damaging-speed = 201

The indicated airspeed in knots above which flap damage may occur, evidenced by slow or inhibited movement. Flaps may be severely damaged or even separate from the aircraft above this airspeed.

blowout-speed = 305

The indicated airspeed in knots above which flaps will be severely damaged or even separate from the aircraft.

[EXITS] Section

The parameters in this section let you configure and adjust the characteristics your aircraft's passenger door or canopy.

Here is the [EXITS] section from Flerk's Corsair with comments removed ...

[EXITS]
number_of_exits = 1
exit_rate.0 = 0.4

number_of_exits = 1

The number of exits on your aircraft, including passenger doors and the canopy.

exit_rate.0 = 0.4

This parameter indexes the exit rate for each aircraft exit. Exit ".0" refers to the first exit, ".1" refers to the second exit, etc..

exit_rate.0 = 0.4

This parameter defines the percent per second this exit will open/close.

   Exit rate value = 1/ time    where time is in seconds.

NOTE
To open/close an exit, hit "Shift+E" on the keyboard. If number_of_exits = 1, this will open the exit defined by exit_rate.0. If you have more exits ( number_of_exits > 1 ), to open the other exits you have to hit "Shift+E," then release those keys and hit the key(s) to open whichever exit(s) you want to open in a fairly short time period. the keyboard number for that exit ... (Keyboard keys, not Number pad keys). For example, to open exit 3, hit "Shift+E" (release) then key "3" on the keyboard.

[FOLDING_WINGS] Section

The parameters in this section let you specify the folding wing characteristics of carrier-based aircraft.

Here is the [FOLDING_WINGS] section from Flerk's Corsair with comments removed ...

[FOLDING_WINGS]
wing_fold_system_type = 1
fold_rates = 0.12,0.11

wing_fold_system_type = 1

This parameter designates whether or not the wings are foldable.

   0 = Wings cannot fold.    1 = Wings are foldable.

fold_rates = 0.12,0.11

This parameter defines the rate in percent per second for each wing to fold/extend.

   Folding rate value = 1/ time    where time is in seconds.

[TAILHOOK] Section

The parameters in this section let you configure arresting gear characteristics of carrier-based aircraft.

Here is the [TAILHOOK] section from Flerk's Corsair with comments removed ...

[TAILHOOK]
tailhook_length = 4.516
tailhook_position = -17.762, 0.0, -1.901
cable_force_adjust = 1.0

tailhook_length = 4.516

This parameter sets the tailhook's length in feet measured from the tailhook_position, which is the distance in feet measured Reference Datum Position (0,0,0).

tailhook_position = -17.762, 0.0, -1.901

This parameter defines X, Y, Z coordinates of the tailhook's pivot point, each of which is the distance in feet measured Reference Datum Position (0,0,0).

cable_force_adjust = 1.0

This parameter "adjusts" the arresting cable tension for this aircraft. A value of 1.05 is a 5% increase in cable tension, while a value of 0.95 is a 5% decrease in cable tension. CFS2 automatically configures the cable tension for this aircraft's mass and normal approach speeds, so the default value of 1.0 is usually correct.

[VIEWS] Section

The parameters in this section let you configure arresting gear characteristics of carrier-based aircraft.

Here is the [VIEWS] section from Flerk's Corsair with comments removed ...

[VIEWS]
eyepoint = -5.97, 0.00, 3.17

eyepoint = -5.97, 0.00, 3.17

This parameter defines the position of the pilot's eyes, measured in feet from the aircraft's Reference Datum Position (0,0,0), and therefore the normal eye position, or viewpoint.

eyepoint = -5.97, 0.00, 3.17

These values represent the longitudinal, lateral, and vertical positions of the pilot's normal eye position measured in feet from the aircraft's Reference Datum Position (0,0,0).

[LSO] Section

The vertical descent speed at which the Landing Signal Officer (LSO) brings an aircraft in to land on the carrier deck is computed by CFS2 based on characteristics specific to that aircraft according to the formula ...

   descent velocity = 1.45 x Stall Speed x LSOAdjustSpeed

Here is the [LSO] section from Flerk's Corsair with comments removed ...

[LSO]
LSOAdjustSpeed = 1.2

LSOAdjustSpeed = 1.2

This parameter defines the scale factor used to adjust the aircraft's landing speed on a carrier approach. A value of 1.2 is a 20% increase in landing speed, while a value of 0.80 is a 20% decrease in landing speed.

WEIGHT_AND_BALANCE CFG File Power Settings