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

Jerome B. Hammack, Thomas C. O'Bryan
naca-tn-4389
Sep 1958


Results are presented 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. At lower Mach numbers the efficiency is higher, being about 85 percent at a Mach number of 0.75. The departure from optimum angle of advance has a small effect for the advance ratios investigated.

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