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NACA-RM-L8E24
Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propelle
Year: 1948
Abstract: Full-scale tests have been made in the Langley 16-foot high-speed tunnel t o determine the aerodynamic characteristics of the NACA 10-(3) (08)-03R propeller. The tests on this propeller were conducted as part of a program to determine the effects of shank design on propeller aerodynamic characteristics.
The tests were made on a 2000-horsepower dynamometer over a range of advance ratio from 0.45 to 3.6. The blade-angle range, measured at the 0.75-radius station, extended from 20° to 50°.
A maximum efficiency of 91.5 percent was attained at 1600 revolutions per minute at a blade angle of 30°. Peak efficiency at a blade angle of 45° was decreased 32 percent by an increase in helical-tip Mach number from 0.80 to 1.2.
The tests were made on a 2000-horsepower dynamometer over a range of advance ratio from 0.45 to 3.6. The blade-angle range, measured at the 0.75-radius station, extended from 20° to 50°.
A maximum efficiency of 91.5 percent was attained at 1600 revolutions per minute at a blade angle of 30°. Peak efficiency at a blade angle of 45° was decreased 32 percent by an increase in helical-tip Mach number from 0.80 to 1.2.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:03:48Z | |
| date available | 2017-09-04T16:03:48Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | RRONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/67115 | |
| description abstract | Full-scale tests have been made in the Langley 16-foot high-speed tunnel t o determine the aerodynamic characteristics of the NACA 10-(3) (08)-03R propeller. The tests on this propeller were conducted as part of a program to determine the effects of shank design on propeller aerodynamic characteristics. The tests were made on a 2000-horsepower dynamometer over a range of advance ratio from 0.45 to 3.6. The blade-angle range, measured at the 0.75-radius station, extended from 20° to 50°. A maximum efficiency of 91.5 percent was attained at 1600 revolutions per minute at a blade angle of 30°. Peak efficiency at a blade angle of 45° was decreased 32 percent by an increase in helical-tip Mach number from 0.80 to 1.2. | |
| language | English | |
| title | NACA-RM-L8E24 | num |
| title | Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propelle | en |
| type | standard | |
| page | 31 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |