1958•Unpublished venueRequires access

Effect of advance ratio on flight performance of a modified supersonic propeller

Jerome B Hammack, Thomas C O'Bryan

Abstract

Note presenting results of a flight investigation to determine the aerodynamic characteristics of a supersonic propeller modified by the incorporation of higher than optimum advance angles. The propeller was designed for a forward Mach number of 0.95, an advance ratio of 3.2, and a power coefficient of 0.42. The efficiency of the propeller is approximately 79 percent at a Mach number of 0.95.

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Key concepts: Propeller, Mach number, Supersonic speed, Aerodynamics, Drag divergence Mach number, Aerospace engineering, Aeronautics, Engineering