Modelling of Unsteady, Incompressible Separation on an Aerofoil Using an Inviscid Flow Algorithm. G.U. Aero Report 8412

Vezza, M. and Galbraith, R.A.M. (1984) Modelling of Unsteady, Incompressible Separation on an Aerofoil Using an Inviscid Flow Algorithm. G.U. Aero Report 8412. Technical Report. Department of Aeronautics and Fluid Mechanics, University of Glasgow.

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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.

Item Type:Research Reports or Papers (Technical Report)
Status:Published
Glasgow Author(s) Enlighten ID:Galbraith, Professor Roderick and Vezza, Dr Marco
Authors: Vezza, M., and Galbraith, R.A.M.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Publisher:Department of Aeronautics and Fluid Mechanics, University of Glasgow
Published Online:08 November 1984
Copyright Holders:Copyright © 1984 Department of Aeronautics and Fluid Mechanics, University of Glasgow
Publisher Policy:Reproduced with the permission of the Department
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