Simulation of Parallel Blade-Vortex Interaction using a Discrete Vortex Method. G.U. Aero Report no. 9832

Qian, L. and Vezza, M. (1998) Simulation of Parallel Blade-Vortex Interaction using a Discrete Vortex Method. G.U. Aero Report no. 9832. Technical Report. Department of Aerospace Engineering, University of Glasgow.

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Abstract

Numerical results are presented for two-dimensional vortex-aerofoil interaction using a grid-free discrete vortex method. The effects of the passing vortex on the surface pressure distribution and hence the aerodynamic force and moment of the aerofoil are examined in detail for a variety of interaction geometries. For some head-on interaction cases, vortex-induced local flow separation is also predicted on the aft part of the aerofoil surfaces. Extensive comparisons are made with other numerical results and the results from the Glasgow University BVI windtunnel test, which show good agreement.

Item Type:Research Reports or Papers (Technical Report)
Status:Published
Glasgow Author(s) Enlighten ID:Vezza, Dr Marco
Authors: Qian, L., and Vezza, M.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Publisher:Department of Aerospace Engineering, University of Glasgow
Copyright Holders:Copyright © 1998 Department of Aerospace Engineering, University of Glasgow

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