Department of Aeronautics and Fluid Mechanics, University of Glasgow
Abstract
Presented in this report is a new method for the prediction of unsteady, incompressible separated flow over a two-dimensional aerofoil. The algorithm was developed from an existing unsteady potential flow model and makes use of an inviscid formulation for the flowfield. The aerofoil is represented by vortex panels of linearly varying strength which are piecewise continuous at the corners. Discrete vortices with finite cores are used to model the separating shear layers. Following a brief summary of unsteady separation modelling, the theoretical framework is presented and the subsequent numerical implementation is discussed in detail. Results are given for flows which tend asymptotically to the steady
state and conclusions are drawn regarding the usefulness of the method
