Definitions of aero coefficients

[GrayGhost 0]

I've searched around the community forums and couldn't find a guide to the aerodynamic coefficients in the aircraft data files. I figured I may as well try to put one together. I realize I may have missed an existing guide and this has been done before.

Anyway, this is what I've figured so far. I'm posting this for peer review and hopefully when can add this information to the knowledge base when it's verified.

Feel free to correct and/or add elaborations on each description, this is by no means comprehensive.

 

Cla = Lift coefficient as a function of AOA

CD0 = Zero-lift drag coefficient

CDL = Total drag coefficient

Cmq = Pitch moment coefficient per radian

Cmad = Pitch moment coefficient per radian AOA ?

Cyb = Side force coefficent per degree of sideslip

Clb = Roll moment coefficient per degree of sideslip

Clp = Roll moment coefficient per roll rate (radians)

Clr = Roll moment coefficient per yaw rate (radians)

Cnb = Yaw moment coefficeint per degee of sideslip

Cnp = Yaw moment coefficient per roll rate (radians)

Cnr = Yaw moment coefficient per yaw rate (radians)

CLaMachTable = Lift coefficient factor (of Cla) vs Mach number

CD0MachTable = Zero-lift drag coefficient factor (of CD0) vs Mach number

CDLAlphaTable = Total drag coefficient vs AOA

CmqMachTable = Pitch moment coefficient vs Mach number

ClbAlphaTable = Clb as a function of AOA

ClpAlphaTable = Clp as a function of AOA

ClrAlphaTable = Clr as a function of AOA

CnpAlphaTable = Cnp as a function of AOA

CnrAlphaTable = Cnr as a function of AOA

XacMachTable = Center-of-pressure distance from wing's neutral point (?) (AOA independent) vs AOA

CLmax = Maximum lift coefficient

AlphaStall = Angle-of-attack where stall begins

AlphaMax = Maximum angle-of-attack while retaining full control?

AlphaDepart = Angle-of-attack where wing departs

Ymac = Lift moment arm about aircraft's longitudinal axis

 

My references: Modern Combat Aircraft Design by Klaus Huenecke, 1987.

http://www.jsbsim.org/CreatingJSBSimAircraft.pdf

[Fubar512 1,350]

CL0 Lift coefficient at zero

angle of attack (AOA)

CLa Lift coefficient due to AOA

CD0 Zero-lift drag coefficient

CDL Drag coefficient due to lift

(induced drag effect)

Cmq Pitching moment due to pitch rate

(pitch damping)

Cmad Pitching moment due to AOA rate

(aero interaction between wings and horiz tail)

Cyb Side force due to sideslip

Cyp Side force due to roll rate

Cyr Side force due to yaw rate

Clb Roll moment due to sideslip

Clp Roll moment due to roll rate

(roll damping)

Clr Roll moment due to yaw rate

Cnb Yaw moment due to sideslip

Cnp Yaw moment due to roll rate

Cnr Yaw moment due to yaw rate

(yaw damping)

CLiftdc Lift due to control surface deflection

CDdc Drag due to control surface deflection

Cydc Side force due to control surface deflection

Cldc Roll moment due to control surface deflection

Cmdc Pitch moment due to control surface deflection

Cndc Yaw moment due to control surface deflection

DeltaStallAlpha Increase in max angle-of-attack before stall

Xac X-location of aerodynamic center

Ymac=Mean Area Chord at "Y" axis

[GrayGhost 0]

Cool! Thanks Fubar!