Calculation of low reynolds number flows at high angles of attack

Calculated results are reported for Eppler and Liebeck airfoils with chord Reynolds numbers ranging from 105 to 5 × 105 and for angles of attack up to stall. They were obtained with an interactive finite-difference boundary-layer method in which the turbulence model employs an extended intermittency expression in the Cebeci and Smith eddy-viscosity model and the location of the onset of transition is determined from linear-stability theory. Comparisons with experiments indicate agreement within measurement uncertainty, except at stall conditions, and close correspondence with the ISES code, which is based on the solution of integral equations.