An Algorithm for the Calculation of the Potential Flow about an Arbitrary Two Dimensional Aerofoil. G.U. Aero Report 8502

Leishman, J.G. and Galbraith, R.A.M. (1985) An Algorithm for the Calculation of the Potential Flow about an Arbitrary Two Dimensional Aerofoil. G.U. Aero Report 8502. Technical Report. Department of Aeronautics and Fluid Mechanics, University of Glasgow.

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Abstract

A vortex panel method has been developed to calculate the potential flow about an arbitrary two dimensional aerofoil or axisymmetric shape at fixed incidence in a steady, uniform, irrotational, incompressible flow. The procedure replaces the contour by a suitably inscribed polygon, on which surface vorticity varies linearly and continuously along the panel and is piecewise continuous at the panel corners. The Neumann boundary condition is satisfied at control points situated at the midpoint of each panel and the classical Kutta condition is specified at the trailing edge by setting the net vorticity there equal to zero. This particular algorithm offers much flexibility in the treatment of a greater range of aerofoil geometries and at higher incidence than other surface singularity methods. Programme flow charts and FORTRAN code listings are given in the User Guide (1).

Item Type:Research Reports or Papers (Technical Report)
Status:Published
Glasgow Author(s) Enlighten ID:Galbraith, Professor Roderick
Authors: Leishman, J.G., 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 © 1985 Department of Aeronautics and Fluid Mechanics, University of Glasgow
Publisher Policy:Reproduced with the permission of the Department
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