Calculating method for multi-stage axial compressors with impulse bladings and constant tip diameter

by Michael Hans Vavra

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• 23 Currently reading

Published 1974 by Naval Postgraduate School in Monterey, Calif .
Written in English

Subjects:

• Compressors,
• Computer programs,
• Aerodynamics,
• Blades

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About the Edition

The report gives an approximate calculating method for the design point performance of multi-stage axial compressors with impulse-type bladings and constant tip diameters. Computing programs for Monroe-1180 programmable calculators are presented to establish the compressor performance and the blading parameters for arbitrary conditions with minimum effort. The report was prepared to permit evaluations of the applicability of such compressors in advanced propulsion units for air-superiority aircraft, or in light-weight lift engines for military VTOL aircraft. (Author)

Edition Notes

Statement	[by] M.H. Vavra
Contributions	Naval Postgraduate School (U.S.)
The Physical Object
Pagination	73 p. :
Number of Pages	73
ID Numbers
Open Library	OL25496307M
OCLC/WorldCa	428441106

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