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A direct viscid-inviscid interaction scheme for the prediction of two-dimensional aerofoil lift and pitching moment in incompressible flow

Part of: 75 year anniversary of Aeronautical Engineering at Glasgow University

Published online by Cambridge University Press:  04 July 2016

F. N. Coton  and
R. A. McD. Galbraith
F. N. Coton
Affiliation:
Department of Aerospace Engineering, University of Glasgow
R. A. McD. Galbraith
Affiliation:
Department of Aerospace Engineering, University of Glasgow
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Summary

This paper presents a method for assessing two-dimensional aerofoil lift and pitching moment 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.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 924 , April 1989 , pp. 132 - 140
Copyright
Copyright © Royal Aeronautical Society 1989 

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