Stall Delay of a NACA0018 Airfoil by Traveling Wave Actuations

Stall Delay of a NACA0018 Airfoil by Traveling Wave Actuations UCHENNA EMMANUEL OGUNKA, TEXAS A&M UNIVERSITY, COLLEGE STATION AMIR MAHDI AKBARZADEH, TEXAS A&M UNIVERSITY, COLLEGE STATION IMAN BORAZJANI, TEXAS A&M UNIVERSITY, COLLEGE STATION DOI: Large eddy simulations (LES) of a low Reynolds number (Re=50,000) flow over a NACA0018 airfoil at the stall angle of attack (AOA) of 15 degrees are performed. The suction side of the airfoil undergoes a surface morphing in the form of backward (opposite to the airfoil’s forward motion) traveling waves. The surface morphing deformations are simulated using our curvilinear immersed boundary (CURVIB) method to control the flow separation and enhance the aerodynamic performance. The amplitude of the morphing is in the range of a = to a = (L: chord length of the airfoil), similar to the range that can be created via piezoelectric actuators. The simulations are alsoperformed for various reduced frequencies (f*