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Analytical investigation of supersonic turbomachinery blading. 2 - Analysis of impulse turbine-blade sectionsSurface Mach numbers, inlet flow angle, and specific heat ratio effects on geometric features of supersonic impulse turbine blade sections in Mach range 1.5 to 5.0
Document ID
19680010807
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Goldman, L. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
April 1, 1968
Subject Category
Auxiliary Systems
Report/Patent Number
NASA-TN-D-4422
Accession Number
68N20276
Funding Number(s)
CONTRACT_GRANT: 128-31-02-25-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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