Quasi-stationary airfoil theory in subsonic compressible flow
Author:
John W. Miles
Journal:
Quart. Appl. Math. 8 (1951), 351-358
MSC:
Primary 76.1X
DOI:
https://doi.org/10.1090/qam/38195
MathSciNet review:
38195
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Abstract: A solution of the integral equation for an oscillating, two-dimensional, thin airfoil in a compressible flow (subsonic and inviscid) is obtained by retaining only first order terms in frequency. The results are applied to the calculation of the damping derivative of a tail in rotary motion about a forward center, and it is shown that the damping is considerably less than that calculated on the basis of stationary airfoil theory. A brief investigation of induction effects shows this reduction to be considerably less for a wing of finite aspect ratio.
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Article copyright:
© Copyright 1951
American Mathematical Society