Modelling of Trailing Edge Separation on Arbitary Two-Dimensional Aerofoils in Incompressible Flow Using an Inviscid Flow Algorithm. G.U. Aero Report 8202

An algorithm for estimating the lift, moment and pressure distribution on arbitary two dimensional aerofoils in incompressible flow is presented. The procedure uses an inviscid analysis of the physics of the real flow, which invokes the application of a linear vortex panel model. The separated wake geometry is determined iteratively, starting from an initial assumption. A boundary layer analysis is not performed, hence the upper surface separation point is a necessary input to the algorithm. Lower surface separation is assumed to occur at the trailing edge. A selection of results and comparison with experimental data is presented. The scatter in the calculated and experimental data values is attributed mainly to the lack of boundary layer displacement and compressibility effects. A fortran code listing of the algorithm is given in the Appendix