NUMERICAL STUDY OF FLOWS IN THE VICINITY OF AIRFOIL TRAILING EDGE

摘要

Flows around NACA0012 airfoil at relatively low Reynolds number are numerically simulated using the Building-Cube method which uses very fine Cartesian mesh. The computed results show that laminar boundary layer on upper surface of the airfoil separates at mid-chord and generates vortices that flows down along the airfoil surface. When a vortex reaches at the trailing edge, it generate a counter-rotating vortex due to the large pressure difference around the sharp trailing edge. At the same time a pressure wave is generated that propagates in all directions from the trailing edge with sonic velocity. Effects of small modifications of airfoil geometry near the trailing edge are also numerically investigated.