STALL CONTROL ON THE NACA 23012 AIRFOIL VIA SINGLE AND DOUBLE SUCTION

Abstract

Flow separation due to adverse pressure gradients is the driving agent for the stalling of wings and consequently aircraft which may lead to disaster. Therefore, this paper focuses on the control of the negative effects of stall on the aerodynamic performance of a NACA 23012 airfoil through the implementation of suction on the upper surface of the airfoil. The suction is carried out at a Reynolds number of 𝑅𝑒=6×106, at angles of attack from 0º to the critical angle. Considering the suction position, and the suction width for a single suction, the capability of suction to control stall is studied. Also, double suction was implemented to determine the effect of multiple slots. The numerical analysis was carried out using the Reynolds Averaged Navier-Stokes equations (RANS) in conjunction with the k-omega (SST) turbulent model. The results from this investigation show that suction is more effective closer to the leading edge by boosting lift by as much as 25% and reducing drag by over 70%. The use of double suction offered no improvements over single suction other than extending the critical angle of attack to 28 º.