Application of finite element code Q3DFLO-81 to turbomachinery flow fields
By: H.D. Schulz ... [et al.].
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1984
Place of publication: Monterey, California
Language: eng
Number of pages: 45
Description: Through flow and blade to blade calculations were made. The Q3DFLO-81 code was operated on an IBM 370-3033 mainframe computer. The flow through a single stage axial research compressor was computed and compared with both probe survey and stage performance map measurements. Swirling flow produced by a vaned out flow generator for a radial diffuser test facility was calculated for both large low speed and small scale high speed versions of the device. Flow through a two dimensional compressor cascade of controlled diffusion blade shapes was calculated and the results compared with experimental data, and with predictions obtained using the NASA code QSONIC. Keywords: Finite Element Code; Turbomachinery Flow Fields; and Through-Flow Calculations.
Notes: Title from cover.

"Prepared for: Naval Air Systems Command, Washington, DC 20361."

"September 1984"--Cover.

"NPS-67-84-005"--Cover.

"Interim report for period 1 October 1983-September 1984"--Cover.

Includes bibliographical references (p. 38-39)

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

Technical report; 1984.

ck/ 4/2/09.

aq/aq cc:9116 02/11/98