An analysis of the off-design performance of shock-in rotor-type supersonic blading is presented. The over-all losses are assumed divided into two groups;normal-shock losses, and external-wave losses. Throughout the range of relative entrance Mach numbers from 1.35 to starting, the largest losses can be attributed to the normal shock. An improvement in performance would be expected with a reduction of the normal-shock losses by the introduction of external compression waves.

CASCADES, EXPERIMENT↗

NASA NTRS1950

Approximate relative-total-pressure losses of an infinite cascade of supersonic blades with finite leading-edge thickness

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Klapproth, John F↗

NASA NTRS1949

Performance of supersonic axial-flow compressors based on one-dimensional analysis

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Wright, Linwood C↗