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The Pressure Rise with Subsonic Mach Number on Fuselages and Nacelles

Published online by Cambridge University Press:  28 July 2016

D. E. Hartley
D. E. Hartley*
Affiliation:
formerlyRoyal Aircraft Establishment, now withHeat Exchangers Ltd.
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Extract

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.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 58 , Issue 524 , August 1954 , pp. 567 - 569
Copyright
Copyright © Royal Aeronautical Society 1954

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References

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