Prediction of airfoil stall at low and high Reynolds numbers

This paper describes an efficient and accurate approach to the prediction of airfoil stall at low and high Reynolds numbers. In this approach, the inviscid flow solutions are coupled with, solutions obtained from the boundary-layer equations with Veldman's interaction law. The boundary-layer method includes an improved Cebeci-Smith eddy-viscosity formulation and computes the onset of the transition location using the e(n)-method of van Ingen and AMO Smith. Results are presented for a wide range of flow conditions, and recommendations are made for the preferred approach for predicting the stall angle and maximum lift coefficient of single and multielement airfoils and wings.