Mixed Transonic Flow over a Wavy Wall with Embedded Shock Waves

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Transonic potential flow over an infinitely-long plane wall corrugated in the form of a streamwise sinusoidal wave has been solved using Murman's finite difference scheme based on small perturbation theory. The range of a transonic similarity parameter, K, is determined in which a subsonic/supersonic mixed flow exist. The structure of the mixed flow is studied in detail for various supercritical free stream Mach numbers. By investigating the transitional transonic drag-rising phenomenon it is found that wave drag is negligibly small in the supercritical parameter range 5.7 ≤ K ≤ 7.02, due to the near-symmetry of locally supersonic flow about the crest of the wavy wall.
Publisher
The Japan Society for Aeronautical and Space Sciences
Issue Date
1983
Citation

Transactions of the Japan Society for Aeronautical and Space Sciences, Vol. 25, No.70, pp. 189-202.

ISSN
0549-3811
URI
http://hdl.handle.net/10203/25276
Appears in Collection
AE-Journal Papers(저널논문)

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