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Airfoils with separation and the resulting wakes

Published online by Cambridge University Press:  21 April 2006

Tuncer Cebeci ,
R. W. Clark ,
K. C. Chang ,
N. D. Halsey  and
K. Lee
Tuncer Cebeci
Affiliation:
Mechanical Engineering Department, California State University, Long Beach, California
R. W. Clark
Affiliation:
Research and Technology, Douglas Aircraft Company, Long Beach, California
K. C. Chang
Affiliation:
Research and Technology, Douglas Aircraft Company, Long Beach, California
N. D. Halsey
Affiliation:
Research and Technology, Douglas Aircraft Company, Long Beach, California
K. Lee
Affiliation:
Mechanical Engineering Department, California State University, Long Beach, California
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Abstract

A viscous/inviscid interaction method is described and has been used to calculate flows around four distinctly different airfoils as a function of angle of attack. It comprises an inviscid-flow method based on conformal mapping, a boundary-layer procedure based on the numerical solution of differential equations and an algebraic eddy viscosity. The results are in close agreement with experiment up to angles close to stall. In one case, where the airfoil thickness is large, small difficulties were experienced and are described. The method is shown to be capable of obtaining results with large flow separation and quantifies the role of transition on the lift coefficient.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 163 , February 1986 , pp. 323 - 347
Copyright
© 1986 Cambridge University Press

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