Two Shock Waves Self-Induced Oscillations over Naca 0012 Airfoil at Low Angles of Attack

Abstract

The self-oscillations mode of two shock waves in a transonic turbulent flow around a NACA 0012 airfoil at low angles of attack is studied numerically. The physical features of the occurrence of self-oscillations are discussed, as well as their difference from other stationary and non-stationary modes of the transonic flow around the NACA 0012 airfoil. An updated map of the transonic turbulent flow regimes around the NACA 0012 airfoil on the plane free-stream Mach number angle of attack is presented.