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Recent Research in Rotor-Noise Reduction
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English
Abstract
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.
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Citation
Sternfeld, H. and Spencer, R., "Recent Research in Rotor-Noise Reduction," SAE Technical Paper 690684, 1969, https://doi.org/10.4271/690684.Also In
References
- 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