Systematic research leading to the development and validation of a 'quiet' full-scale tail rotor is described in this paper. Hover performance and acoustic test results acquired on the Sikorsky tail rotor whirl test facility, and some early results from the just-concluded flight tests are provided. The results show that substantial reduction in noise signature can be achieved simultaneously with improvements in performance when advances in aerodynamic and aeroacoustic technologies are judiciously applied.
Development and validation of 'quiet tail rotor' technology
1991-01-01
Conference paper
No indication
English
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