The Pressure Rise with Subsonic Mach Number on Fuselages and Nacelles-Reference-Cited by-同舟云学术

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The Pressure Rise with Subsonic Mach Number on Fuselages and Nacelles

Published:1954-08 Issue:524 Volume:58 Page:567-569
ISSN:0368-3931
Container-title:The Journal of the Royal Aeronautical Society
language:en
Short-container-title:J. R. Aeronaut. Soc.

Author:

Hartley D. E.

Abstract

In treating the compressible subsonic flow by the Prandtl-Glauert method as extended by Göthert, the velocity increment v in the direction of the main stream is found to be 1/β2 times the corresponding velocity increment va on the analogous body in incompressible flow; the analogous body being obtained by reducing the lateral dimensions of the real body in the ratio β:1.

Publisher

Cambridge University Press (CUP)

Reference11 articles.

1. Reissner E. (1949). On Compressibility Corrections for Subsonic Flow over Bodies of Revolution. N.A.C.A. T.N. 1815, 1949.

2. Matthews C. W. (1952). A Comparison of the Experimental Subsonic Pressure Distributions about several Bodies of Revolution with Pressure Distributions computed by means of the Linearised Theory N.A.C.A. T.N. 2519, 1952.

3. Oswatitsch K. (1950). The Effect of Compressibility on the Flow around Slender Bodies of Revolution. Swedish Report KTH—Aero T.N. 12, 1950.

4. Compressibility Corrections for Bodies of Revolution

5. The subsonic flow about a body of revolution

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