On the Design of Thin Subsonic Airfoils

[+] Author and Article Information
W. C. Chin

Aerodynamics Research Group, Boeing Commercial Airplane Company, Mall Stop 3N-29, P. O. Box 3707, Seattle, Wash. 98124

J. Appl. Mech 46(1), 6-8 (Mar 01, 1979) (3 pages) doi:10.1115/1.3424530 History: Received May 01, 1978; Revised August 01, 1978; Online July 12, 2010


The inverse problem, which determines an airfoil geometry given some specified surface pressure, is considered in the subsonic, thin-airfoil limit. The full governing equations are expanded in powers of the thickness ratio and solved to second-order. The two sequential formulations contain free parameters, which are fixed by invoking “Kutta-type” conditions related to trailing edge closure. The correctness of the basic approach is demonstrated by using known classical examples for the simpler first-order problem.

Copyright © 1979 by ASME
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