Numerical prediction of laminar-turbulent transition on an airfoil

摘要

An original technology of stability analysis of an airfoil boundary layer is presented in this paper. The technology includes an extraction of the boundary layer from the results of laminar flow computations, the computation of neutral curves and increments of Tollmien-Schlichting waves, and the computation of the location of laminar-turbulent transition zone by the e~N-method for a given set of freestream turbulence levels. To be specific, we consider the flow around the NACA23012 airfoil with zero angle of attack at moderate Reynolds numbers.