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Unsteady Flow In A Supersonic Cascade With ShocksOperating range of turbomachinery for which stability calculated extended. TIPS (Two In-Passage Shocks) calculates unsteady lifts and moments on compressor blade if relative mach number supersonic and if two shock waves in blade passage. Written in FORTRAN IV and run on IBM 3033 with 370TSS operating system.
Document ID
19880000291
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Molls, Frank B. (NASA Lewis Research Center, Cleveland, Ohio.)
Braun, Willis H. (NASA Lewis Research Center, Cleveland, Ohio.)
Date Acquired
August 13, 2013
Publication Date
May 1, 1988
Publication Information
Publication: NASA Tech Briefs
Volume: 12
Issue: 5
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LEW-14339
Report Number: LEW-14339
ISSN: 0145-319X
Accession Number
88B10291
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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