Abstract
In this research, three-parameter numerical optimization of aerodynamic characteristics of an airfoil at high angle of attack is carried out. The separation region is reduced with two types of suction/blowing usage: single blowing function jet and combined suction and blowing jets. Genetic algorithm is used to optimize the three parameters of the suction/blowing jet strength, jet angle and jet location. The objective of this investigation was to reduce the high separation region over the NACA0012 airfoil to enhance its aerodynamic characteristics. The time-averaged compressible Navier–Stokes equations with Spalart–Allmaras turbulence model are solved along with optimization algorithm. The lift-to-drag ratio is increased up to 80 % with respect to the uncontrolled flow field.
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