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Aerodynamic Design of Axial-flow CompressorsAvailable experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of the magnitude of the reference total-pressure loss and the reference deviation and incidence angles for conventional blade profiles. These relations are developed in simplified forms readily applicable to compressor design procedures.
Document ID
19930089244
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Date Acquired
August 16, 2013
Publication Date
August 1, 1956
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-E56B03a
Accession Number
93R18534
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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