Cruise Noise Of The Sr 2 Propeller Model In A Wind Tunnel
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Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 30 |
Release | : 2018-07 |
Genre | : |
ISBN | : 9781722138219 |
Noise data on the SR-2 model propeller were taken in the NASA Lewis Research Center 8- by 6-Foot Wind Tunnel. The maximum blade passing tone rises with increasing helical tip Mach number to a peak level at a helical tip Mach number of about 1.05; then it remains the same or decreases at higher helical tip Mach numbers. This behavior, which has been observed with other propeller models, points to the possibility of using higher propeller tip speeds to limit airplane cabin noise while maintaining high flight speed and efficiency. Noise comparisons of the straight-blade SR-2 propeller and the swept-blade SR-7A propeller showed that the tailored sweep of the SR-7A appears to be the cause of both lower peak noise levels and a slower noise increase with increasing helical tip Mach number. Dittmar, James H. Glenn Research Center RTOP 535-03-01...
Author | : James H. Dittmar |
Publisher | : |
Total Pages | : 27 |
Release | : 1989 |
Genre | : Aerodynamic noise |
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Total Pages | : 32 |
Release | : 1989 |
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Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 38 |
Release | : 2018-08-16 |
Genre | : |
ISBN | : 9781725577701 |
The noise of advanced high speed propeller models measured in the NASA 8- by 6-foot wind tunnel has been compared with model propeller noise measured in another tunnel and with full-scale propeller noise measured in flight. Good agreement was obtained for the noise of a model counterrotation propeller tested in the 8- by 6-foot wind tunnel and in the acoustically treated test section of the Boeing Transonic Wind Tunnel. This good agreement indicates the relative validity of taking cruise noise data on a plate in the 8- by 6-foot wind tunnel compared with the free-field method in the Boeing tunnel. Good agreement was also obtained for both single rotation and counter-rotation model noise comparisons with full-scale propeller noise in flight. The good scale model to full-scale comparisons indicate both the validity of the 8- by 6-foot wind tunnel data and the ability to scale to full size. Boundary layer refraction on the plate provides a limitation to the measurement of forward arc noise in the 8- by 6-foot wind tunnel at the higher harmonics of the blade passing tone. The use of a validated boundary layer refraction model to adjust the data could remove this limitation. Dittmar, James H. Glenn Research Center NASA-TM-101976, E-4676, NAS 1.15:101976, AIAA PAPER 89-1059 RTOP 535-03-01...
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Total Pages | : 56 |
Release | : 1987 |
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Author | : James H. Dittmar |
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Total Pages | : |
Release | : 1989 |
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Author | : James H. Dittmar |
Publisher | : |
Total Pages | : 20 |
Release | : 1981 |
Genre | : Propellers, Aerial |
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Total Pages | : 26 |
Release | : 1985 |
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Total Pages | : 1572 |
Release | : 1992 |
Genre | : Aeronautics |
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Total Pages | : 92 |
Release | : 1982 |
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