Experimental Investigation of Effects of Blade Section Camber and Planform Taper on Rotor Hover Performance
Final rept. Oct 1970-Oct 1971
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT
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An experimental and analytical investigation was conducted to determine the effects of blade section camber and blade planform taper on helicopter rotor hover performance and to assess the accuracy of several theoretical methods in predicting such performance. The tests were conducted using small scale model rotors nominally 4 feet in diameter operating in and out of ground effect at full-scale tip speeds. The NACA 23112 airfoil, which is a section specifically designed to produce very low pitching moments such as required for helicopter blade applications, was selected for the cambered blade. A nominal taper ratio of 21 was selected for the tapered blade tests.
- Fluid Mechanics