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NASA-CR-2299
Pressure recovery performance of conical diffusers at high subsonic Mach numbers
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:57:21Z | |
| date available | 2017-09-04T16:57:21Z | |
| date copyright | 01/01/1973 | |
| date issued | 1973 | |
| identifier other | XGNKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/120874 | |
| description abstract | The pressure recovery performance of conical diffusers has been measured for a wide range of geometries and inlet flow conditions. The approximate level and location (in terms of diffuser geometry of optimum performance were determined. Throat Mach numbers from low subsonic (m sub t equals 0.2) through choking (m sub t equals 1.0) were investigated in combination with throat blockage from 0.03 to 0.12. For fixed Mach number, performance was measured over a fourfold range of inlet Reynolds number. Maps of pressure recovery are presented as a function of diffuser geometry for fixed sets of inlet conditions. The influence of inlet blockage, throat Mach number, and inlet Reynolds number is discussed. | |
| language | English | |
| title | NASA-CR-2299 | num |
| title | Pressure recovery performance of conical diffusers at high subsonic Mach numbers | en |
| type | standard | |
| page | 154 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1973 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | CONFIGURATIONS | |
| subject keywords | CONICAL | |
| subject keywords | DIFFUSERS | |
| subject keywords | DISTRIBUTION | |
| subject keywords | EQUATIONS | |
| subject keywords | FLOW | |
| subject keywords | INLET | |
| subject keywords | PRESSURE | |
| subject keywords | RECOVERY | |
| subject keywords | SUBSONIC |
