Aerodynamic performance of a 0.27-scale model of an AH-64 helicopter with baseline and alternate rotor blade sets

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National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990 - Transportation - 21 pages
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Performance of a 0.27-scale rotor model designed for the AH-64 Apache helicopter (alternate rotor) was measured in hover and forward flight compared with an AH-64 baseline rotor model. Thrust, rotor tip Mach number, advance ratio, and ground proximity were varied. In hover, at a nominal thrust coefficient of 0.0064, the alternate rotor used about 6.4% less power than the baseline rotor. The corresponding thrust increase at this representative hover power condition was approximately 4.5%, which represents an equivalent full-scale increase in lift capability of about 660 lb. Comparable results were noted in forward flight, except for the high-thrust, high-speed cases investigated (Advance ratio = 0.30), where the baseline rotor was slightly superior. Reduced performance at the higher thrusts and speeds was probably caused by Reynolds number effects and blade elasticity differences. Keywords: Rotor blades rotary wings; Blade tips; Attack helicopters; Helicopter rotor performance; Model rotor testing; Tapered rotor blades; Ground effects. (edc).

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