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Simulation of parallel blade–vortex interaction using a discrete vortex method

Published online by Cambridge University Press:  04 July 2016

L. Qian  and
M. Vezza
L. Qian
Affiliation:
Department of Aerospace EngineeringUniversity of GlasgowGlasgow, UK
M. Vezza
Affiliation:
Department of Aerospace EngineeringUniversity of GlasgowGlasgow, UK
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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 wind-tunnel test, which show good agreement.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1029 , November 1999 , pp. 537 - 543
Copyright
Copyright © Royal Aeronautical Society 1999 

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