Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig
By: by M.H.Vavra
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1970
Place of publication: Monterey, California
Language: eng
Number of pages: 58
Subjects: Compressors; Aerodynamics; Blades
Description: The report deals with the aerodynamic design of an axial compressor stage with symmetrical bladings for a research program to investigate tip clearance effects in a three-stage compressor. It establishes the blading data and the stage performance with an iterative three-dimensional approach, and gives criteria for the drive and the flow measuring device of the test unit. The calculated distributions of the flow properties in the stage will be used for future comparisons with test data. (Author)
Notes: Title from cover.

"1 September 1970"--Cover.

"NPS-57VA70091A"--Cover.

DTIC Identifiers: Design criteria.

Author(s) key words: Axial compressor blading, test rig, aerodynamic design, three-dimensional.

Includes bibliographical references (p. 32)

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

Technical report; 1970.