GrayGhost Posted September 2, 2007 Posted September 2, 2007 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 Quote
+Fubar512 Posted September 3, 2007 Posted September 3, 2007 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 Quote
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