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Some Effects of Compressibility on the Flow Through Fans and TurbinesThe laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressure ratio exists. One of these nonideal operating ranges is analogous to a similar type in incompressible flow. The other is characteristic only of compressible flow. The effect of variable axial-flow area is treated. Some implications of the basic conservation laws in the case of nonideal flow through cascades are discussed.
Document ID
19930091917
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Report
Authors
Perl, W. (National Advisory Committee for Aeronautics. Aircraft Engine Research Lab. Cleveland, OH, United States)
Epstein, H. T. (National Advisory Committee for Aeronautics. Aircraft Engine Research Lab. Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1946
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-TR-842
Accession Number
93R21207
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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