Some Effects of Compressibility on the Flow Through Fans and Turbines
Description:
"The 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 pressur…
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Date:
August 1, 1945
Creator:
Perl, W. & Epstein, H. T.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department