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NACA-RM-L51E02
Flight determination of drag and pressure recovery of a nose inlet of parabolic profile at Mach numbers from 0.8 to 1.7
Year: 1951
Abstract: A ducted model having a nose inlet whose external contour was defined by a parabolic arc was flight-tested at zero angle of attack. External drag coefficient and total-pressure recovery at the end of the diffuser were measured over a range of Mach numbers from 0.8 to 1.7 and a range of mass-flow ratios from 0.23 to 1.0. The Reynolds number based on the 10-inch body diameter varied from about 4 x 106 to 9 x 106.
At supersonic speeds, the parabolic inlet model had about the same drag coefficient as the basic parabolic body from which it was derived. At low supersonic speeds, the drag of the parabolic inlet was about the same as that of an NACA 1-40-250 nose inlet previously tested. At M = 1.7, however, the drag coefficient of the NACA 1-40-250 inlet model was 37 percent greater than that of the parabolic inlet model.
At supersonic speeds, the parabolic inlet model had about the same drag coefficient as the basic parabolic body from which it was derived. At low supersonic speeds, the drag of the parabolic inlet was about the same as that of an NACA 1-40-250 nose inlet previously tested. At M = 1.7, however, the drag coefficient of the NACA 1-40-250 inlet model was 37 percent greater than that of the parabolic inlet model.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:18:57Z | |
| date available | 2017-09-04T15:18:57Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | ASONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/18680 | |
| description abstract | A ducted model having a nose inlet whose external contour was defined by a parabolic arc was flight-tested at zero angle of attack. External drag coefficient and total-pressure recovery at the end of the diffuser were measured over a range of Mach numbers from 0.8 to 1.7 and a range of mass-flow ratios from 0.23 to 1.0. The Reynolds number based on the 10-inch body diameter varied from about 4 x 106 to 9 x 106. At supersonic speeds, the parabolic inlet model had about the same drag coefficient as the basic parabolic body from which it was derived. At low supersonic speeds, the drag of the parabolic inlet was about the same as that of an NACA 1-40-250 nose inlet previously tested. At M = 1.7, however, the drag coefficient of the NACA 1-40-250 inlet model was 37 percent greater than that of the parabolic inlet model. | |
| language | English | |
| title | NACA-RM-L51E02 | num |
| title | Flight determination of drag and pressure recovery of a nose inlet of parabolic profile at Mach numbers from 0.8 to 1.7 | en |
| type | standard | |
| page | 24 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |