NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Design of Multistage Axial-Flow CompressorsProgram developed for computing aerodynamic design of multistage axialflow compressor and associated blading geometry input for internal flow analysis. Aerodynamic solution gives velocity diagrams on selected streamlines of revolution at blade row edges. Program written in FORTRAN IV.
Document ID
19830000191
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Crouse, J. E. (U.S. Army Aviation Research and Development Command)
Gorrell, W. T.
Date Acquired
August 11, 2013
Publication Date
October 1, 1983
Publication Information
Publication: NASA Tech Briefs
Volume: 7
Issue: 4
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LEW-13505
Accession Number
83B10191
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.

Related Records

There are no records associated with this record.
No Preview Available