Effects of Compressibility, Pitch Rate and Reynolds Number on Unsteady IncipientLeading-Edge Boundary Layer Separation Over a Pitching Airfoil

摘要

The effects of compressibility, pitch rate and Reynolds number on the initialstages of 2-D unsteady separation of laminar subsonic flow over a pitching NACA-0012 airfoil have been studied numerically. Computations have been performed using two separate algorithms (structured grid algorithm of Beam and Warming, and unstructured grid algorithm employing flux-difference splitting method of Roe) for the compressible laminar Navier-Stokes equations. The simulations show the appearance of a primary recirculating region near the leading edge, followed by a secondary and tertiary recirculating regions.