Calculating method for multi-stage axial compressors with impulse bladings and constant tip diameter
By: [by] M.H. Vavra
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1974
Place of publication: Monterey, Calif
Language: eng
Number of pages: 73
Subjects: Compressors; Computer programs; Aerodynamics; Blades
Description: 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)
Notes: Title from cover.

"Prepared for: naval Air Systems Command, Code 310A, Washington, D.C. 20360"--Cover.

"March 1974"--Cover.

"NPS-57Va74031"--Cover.

"Interim report (Period July 1973 - June 1974)

Author(s) subject terms: Multi-stage axial compressors, impulse bladings, performance calculations, use of electronic programmable hand calculators.

Includes bibliographic references.

"Approved for public release; distribution unlimited"--Cover.

Technical report; 1974.