aerodynamic derivatives coefficients

eli123 · March 15, 2022, 07:05

Hello all,

Is there a way to compute the aerodynamic derivatives coefficients
(stability derivatives) for an airfoil such as: Cmalpha, Clp, Cnr, Cmq ?

Regards,

Eli

PENGGEGE777 · March 16, 2022, 03:28

Hi, I have little experience on how to compute aerodynamics deriveatives in SU2, but I have an ideal.

Take CL_alpha as an example, you can compute CL with different alpha, and then calculate CL_alpha by yourself, i.e., CL_alpha = (CL(alpha_1)-CL(alpha_2))/(alpha_1-alpha_2).

Hope this makes you more close to the solution.

March 15, 2022, 07:05	aerodynamic derivatives coefficients	#1
eli123 New Member anonymous Join Date: Jan 2014 Posts: 9 Rep Power: 12	Hello all, Is there a way to compute the aerodynamic derivatives coefficients (stability derivatives) for an airfoil such as: Cmalpha, Clp, Cnr, Cmq ? Regards, Eli

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March 16, 2022, 03:28		#2
PENGGEGE777 Member PENG YAN Join Date: Jul 2021 Location: Italy Posts: 34 Rep Power: 5	Hi, I have little experience on how to compute aerodynamics deriveatives in SU2, but I have an ideal. Take CL_alpha as an example, you can compute CL with different alpha, and then calculate CL_alpha by yourself, i.e., CL_alpha = (CL(alpha_1)-CL(alpha_2))/(alpha_1-alpha_2). Hope this makes you more close to the solution.