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

Coton, F.N. and Galbraith, R.A.M. (1987) A Direct Viscid-Inviscid Interaction Scheme for the Prediction of 2-Dimensional Aerofoil Performance in Incompressible Flow. G.U. Aero Report 8701. Technical Report. Department of Aeronautics and Fluid Mechanics, University of Glasgow.

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Abstract

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.

Item Type:Research Reports or Papers (Technical Report)
Status:Published
Glasgow Author(s) Enlighten ID:Coton, Professor Frank and Galbraith, Professor Roderick
Authors: Coton, F.N., 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
Copyright Holders:Copyright © 1987 Department of Aeronautics and Fluid Mechanics, University of Glasgow
Publisher Policy:Reproduced with the permission of the Department

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