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Recent Research in Rotor-Noise Reduction
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1969 by SAE International in United States
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Helicopter design trends towards increased blade loadings and higher tip speeds have resulted in generation of higher levels of rotor noise. This paper describes experimental programs to establish operating limits which, if observed, will result in rotary-wing aircraft with subjectively acceptable acoustical signatures.
CitationSternfeld, H. and Spencer, R., "Recent Research in Rotor-Noise Reduction," SAE Technical Paper 690684, 1969, https://doi.org/10.4271/690684.
- Sternfeld H. Schairer J. O. Study of Rotor Blade Tip Vortex Geometry for Noise and Airfoil Application Contract N0019-68-C-0608 The Boeing Company, Vertol Division June 1961
- CH-47 Advanced Geometry Blade U.S. Army Contract DAAJ02-67-C-0072 The Boeing Company, Vertol Division