A Design Procedure to Modify the Trailing Edge Upper Surface Pressure Gradient of a Given Aerofoil. G.U. Aero Report 8408

Niven, A.J. and Galbraith, R.A.M. (1984) A Design Procedure to Modify the Trailing Edge Upper Surface Pressure Gradient of a Given Aerofoil. G.U. Aero Report 8408. Technical Report. Department of Aeronautics and Fluid Mechanics, University of Glasgow.

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Abstract

Summary: Little is known about the detailed flow on the upper surface of aerofoils, prone to trailing edge separation, during the process of dynamic stall. The present report describes a method whereby the pressure gradient on the trailing edge upper surface of a given aerofoil may be modified to either enhance or reduce such separations, for a given section, whilst retaining the leading edge pressure distribution.

Item Type:Research Reports or Papers (Technical Report)
Status:Published
Glasgow Author(s) Enlighten ID:Galbraith, Professor Roderick
Authors: Niven, A.J., 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 © 1984 Department of Aeronautics and Fluid Mechanics, University of Glasgow
Publisher Policy:Reproduced with the permission of the Department
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