Preliminary investigation of supersonic diffusers /
by Arthur Kantrowitz and Coleman duP. Donaldson.
Description
- Language(s)
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English
- Published
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Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1945.
- Summary
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Summary: The deceleration of air from supersonic velocities in channels has been studied. It has become apparent that a normal shock in the diverging part of the diffuser is probably necessary for stable flow, and ways of minimizing the intensity of this shock have been developed. The effect of various geometrical parameters, especially contraction ratio in the entrance region, on the performance of supersonic diffusers has been investigated. By the use of these results, diffusers were designed which, starting without initial boundary layer, recovered 90 percent of the kinetic energy in supersonic air streams up to a Mach number of 1.85.
- Note
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"CLASSIFIED DOCUMENT This document contains classified information affecting the National Defense of the United States within the meaning of the Espionage Act, USC 50:31 and 32. Its transmission or the revelation of its contents in any manner to an unauthorized person is prohibited by law. Information so classified may be imparted only to persons in the military and naval Services of the United States, appropriate civilian officers and employees of the Federal Government who have a legitimate interest therein, and to United States citizens of known loyalty and discretion who of necessity must be informed thereof."
"Report date May 1945."
"Advance Confidential Report L5D20."
Also available in electronic format.
- Physical Description
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13, [10] p. :
ill. ;
28 cm.
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