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NACA-TN-3394
Low-speed investigation of the effects of angle of attack on the pressure recovery of a circular nose inlet with several lip shapes
Year: 1955
Abstract: Wind-tunnel tests wee conducted to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0° to 25°.
A sharp inlet lip having a wedge angle of 7-½° was tested in addition to two circular-arc profiles and two elliptical profiles formed within the wedge of the sharp lip by cutting back the leading edge various amounts. It was found that for a given amount of cutback, the circumferential variation of total pressure at the measuring station (the simulated entrance to a turbojet-engine compressor) was about the same with either an elliptical- or circular-arc-profile lip; however, the average total-pressure recovery characteristics were better with the elliptical-profile lip.
A sharp inlet lip having a wedge angle of 7-½° was tested in addition to two circular-arc profiles and two elliptical profiles formed within the wedge of the sharp lip by cutting back the leading edge various amounts. It was found that for a given amount of cutback, the circumferential variation of total pressure at the measuring station (the simulated entrance to a turbojet-engine compressor) was about the same with either an elliptical- or circular-arc-profile lip; however, the average total-pressure recovery characteristics were better with the elliptical-profile lip.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:53:04Z | |
| date available | 2017-09-04T16:53:04Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | WUNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/116465 | |
| description abstract | Wind-tunnel tests wee conducted to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0° to 25°. A sharp inlet lip having a wedge angle of 7-½° was tested in addition to two circular-arc profiles and two elliptical profiles formed within the wedge of the sharp lip by cutting back the leading edge various amounts. It was found that for a given amount of cutback, the circumferential variation of total pressure at the measuring station (the simulated entrance to a turbojet-engine compressor) was about the same with either an elliptical- or circular-arc-profile lip; however, the average total-pressure recovery characteristics were better with the elliptical-profile lip. | |
| language | English | |
| title | NACA-TN-3394 | num |
| title | Low-speed investigation of the effects of angle of attack on the pressure recovery of a circular nose inlet with several lip shapes | en |
| type | standard | |
| page | 31 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |