Flow into a transonic compressor rotor
Subtitle: part 1 -- analysis
By: [by] R. P. Shreeve
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1974
Place of publication: Monterey, Calif
Language: eng
Number of pages: 30
Subjects: Compressors; Mathematical models; Fluid dynamics; Blades
Description: An analytical representation is given for the axisymmetric 2-dimensional flow field at the face of a transonic rotor.  Streamlines computed for irrotational inviscid flow are closely approximated using a curve-fitting technique, which is described, and boundary layer blockage is then introduced.  With the inlet flow so represented, the conditions relative to the rotor blading of the TRANSX compressor are calculated as a function of the radius and graphed as a function of flow rate and rotor speed.  The purpose of this report is to both document calculations carried out for the TRANSX comp5ressor and to record useful analytical techniques and short programs developed using the Hewlett-Packard Model 9830A calculator. (Author)
Notes: Title from cover.

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

"August 1974"--Cover.

"NPS-57Sf74081"--Cover.

"Interim report for period July 1973 - June 1974."

Author(s) subject terms: Transonic compressors, compressible inlet flow fields, programmable calculators for engineering analysis.

Includes bibliographical references (p. 12)

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

Technical report; 1974.