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Results from Performance and Noise Tests of Model Scale Propellers
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English
Abstract
This paper summarizes some of the results obtained in a study of two .25 scale propellers tested in the Quiet Flow Facility at the NASA Langley Research Center. Both performance and noise measurements were made over advance ratios from .4 to 1.3, for thrust loadings up to 22 lbs/ft2 and tip Mach numbers up to .82. These data were obtained for validation of noise and performance prediction theories. Scale effects on performance were also examined using data obtained from other tests at .566 and full scale for the two propellers. Finally, the effect on performance and noise of a wake entering the disk plane was examined.
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Authors
Citation
Block, P. and Martin, R., "Results from Performance and Noise Tests of Model Scale Propellers," SAE Technical Paper 830730, 1983, https://doi.org/10.4271/830730.Also In
References
- FARASSAT, F. Advanced Theoretical Treatment of Propeller Noise Lecture Series 1982-08, von Karman Institute for Fluid Dynamics 1982
- BOCCI, A. J. A New Series of Aerofoil Sections Suitable for Aircraft Propellers Aeronautical Quarterly 28 1977 59 73
- BLOCK, P. J. W. Operational Evaluation of a Propeller Test Stand in the Quiet Flow Facility at Langley Research Center NASA TM 84523 1982
- JERACKI, R. J. MITCHELL, G. A. Low and High Speed Propellers for General Aviation - Performance Potential and Recent Wind Tunnel Tests NASA TM 81745. April 1981 (Also SAE 810601 1982
- CARLSON, L. A. Transonic Airfoil Flow- field Analysis Using Cartesian Coordinates NASA CR 2577 1975
- JACOBS, E. N. SHERMAN, A. Airfoil Section Characteristics as Affected by Variations of the Reynolds Number NACA Rept. No. 586 1937
- NYSTROM, P. A. FARASSAT, F.: A Numerical Technique for Calculation of the Noise of High Speed Propellers with Advanced Blade Geometry NASA TP 1662 1980