An interactive boundary-layer method, together with the e~n-approach to the calculation of transition, has been used to predict the compressibility effect on airfoil stall at low Mach numbers. Two separate inviscid methods - a panel method with compressibility corrections and a full potential method-are used to compute the external velocity distribution needed in the solution of the compressible boundary-layer equations. The turbulence model is based on the Cebeci-Smith algebraic eddy-viscosity formulation with improvements for strong pressure gradient effects. Comparison of calculated results obtained with the full potential method indicate excellent agreement with experiment for a wide range of angles of attack, including stall. The study also shows that enen though the compressibility corrections to the panel method are adequate at small to moderate angles of attack, they are not satisfactory at higher angles of attack, expecially near stall.
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