Department of Aeronautics and Fluid Mechanics, University of Glasgow
Abstract
Summary:
A new model is presented for the calculation of the incompressible,
inviscid flow around an arbitrary aerofoil undergoing unsteady motion.
The technique was developed from the steady flow algorithm of Leishman and Galbraith (1) in which use was made of a linear distribution of panel vorticity. The procedure is in the same class as that of Basu and Hancock (2) but, because of the particular approach to the manner of specifying the shed vorticity, only a set of linear simultaneous equations needs be solved, unlike the method of reference (2), complicated by the necessary solution of a quadratic.
A brief history of unsteady flow modelling is given in the introduction, followed by the mathematical details of the current method. Results are presented and discussed for a number of cases which clearly illustrate relevant characteristics of unsteady flow
