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A discrete vortex method for the non-steady separated flow over an airfoil

Published online by Cambridge University Press:  20 April 2006

J. Katz
J. Katz
Affiliation:
Ames Research Center, NASA, Moffett Field, California 94035NRC Associate. Present address: Dept. Mechanical Engineering, Technion, Haifa, Israel.
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Abstract

A discrete vortex method was used to analyse the separated non-steady flow about a cambered airfoil. The foil flow modelling is based on the thin lifting-surface approach, where the chordwise location of the separation point is assumed to be known from experiments or flow-visualization data. Calculated results provided good agreement when compared with the post-stall aerodynamic data of two airfoils. Those airfoil sections differed in the extent of travel of the separation point with increasing angle of attack. Furthermore, the periodic wake shedding was analysed and its time-dependent influence on the airfoil was investigated.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 102 , January 1981, pp. 315 - 328
Copyright
© 1981 Cambridge University Press

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