A Direct Viscid-Inviscid Interaction Scheme for the Prediction of 2-Dimensional Aerofoil Performance in Incompressible Flow. G.U. Aero Report 8701

Summary: This paper presents a method for assessing two-dimensional aerofoil performance characteristics including trailing edge and gross laminar separation. The model used is a direct viscid-inviscid interaction scheme based on a vortex panel method with boundary layer corrections and an inviscidly modelled wake. The Integral boundary layer methods adopted behave well in the region of separation and thus, good comparisons with measured separation characteristics are obtained. Generally the predictions of lift and pitching moment may be considered to be within the experimental error, but where this is not the case, the applicability of the modelling technique is discussed