A question about airfoil optimization using Genetic Algorithm

For Airfoil optimization using genetic algorithm .. How can I obtain a equation that Links my control points of the airfoil to the objectives like cl and cd .. I really don't know how to link them together through equation or implement Control points in the objective function

Answer 1

[Alan Weiss]

Assuming that you are using Simulink to simulate the airfoil, this answer might be relevant.

I really don't know anything about Simulink though, so will not be able to provide any further help.

Alan Weiss

MATLAB mathematical toolbox documentation

Answer 2

[Fernando Echeverria]

Hello,

I think you should go outside Matlab in the middle. You need to link your Matlab code to a panel method code or CFD: Change the geometry in Matlab, feed the aerodynamic code, launch it and read the solution in Matlab.

Best regards

Answer 3

[yassine khalil]

You can use XFOIL as script in Matlab. XFOIL is able to generate the Cl and Cd and then the objective function

[Hesham Shaarawy]

Can you please elaborate on how XFOIL can provide the objective function, once the Cl and Cd have been obtained ?