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RESEARCH PAPERS

Contact Problems Involving the Flow Past an Inflated Aerofoil

[+] Author and Article Information
J.-M. Vanden-Broeck

Department of Mathematics, Stanford University, Stanford, Calif. 94305

J. Appl. Mech 49(2), 263-265 (Jun 01, 1982) (3 pages) doi:10.1115/1.3162078 History: Received April 01, 1981; Online July 21, 2009

Abstract

Steady potential flow around a two-dimensional inflated airfoil is considered. The aerofoil consists of a flexible and inextensible membrane which is anchored at both leading and trailing edges. The flow and the aerofoil shape are determined as functions of the angle of attack α, the cavitation number γ, and the Weber number λ. When γ decreases to a critical value γ0 (α, λ), opposite sides of the membrane become tangent to each other at the trailing edge. For γ < γ0 the aerofoil is partially collapsed near the trailing edge. The length of the region of collapse increases as γ decreases and for γ = −∞, the aerofoil is completely collapsed. The shape of the aerofoil and the value of γ0 are determined analytically by a perturbation solution for λ small. Graphs of the results are presented.

Copyright © 1982 by ASME
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