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Performance of a transonic compressor rotor with an aspect ratio of 6.5The overall and blade-element performances and the aerodynamic design parameters of a transonic rotor with an aspect ratio of 6.5, designed to investigate the effects of aspect ratio on range and performance are presented. The rotor was designed for a total-pressure ratio of 1.53, an efficiency of 0.898, and a weight flow of 67.76 pounds per second.
Document ID
19740018136
Document Type
Other - NASA Technical Note (TN)
Authors
Reid, L.
(NASA Lewis Research Center Cleveland, OH, United States)
Tysl, E. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
E-7641
NASA-TN-D-7662
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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