درباره ما
NACA-RM-E51L26
Some observations of shock-induced turbulent separation on supersonic diffusers
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:25:31Z | |
| date available | 2017-09-04T15:25:31Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | NLMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/26080 | |
| description abstract | A survey of experimental data at supersonic speed indicated that shock-induced separation of a turbulent boundary layer will result for Mach numbers of approximately 1.33 or greater when a theoretical stream static-pressure-rise ratio of approximately 1.89 occurs across a shock interacting with the boundary layer. The significance of this tentative criterion for turbulent boundary-layer separation is discussed with respect to the design of supersonic diffusers. | |
| language | English | |
| title | NACA-RM-E51L26 | num |
| title | Some observations of shock-induced turbulent separation on supersonic diffusers | en |
| type | standard | |
| page | 16 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMICS | |
| subject keywords | BOUNDARY | |
| subject keywords | CONTROL | |
| subject keywords | DIFFUSERS | |
| subject keywords | FLOW | |
| subject keywords | INTERNAL | |
| subject keywords | LAYER | |
| subject keywords | SUPERSONIC | |
| subject keywords | TURBULENT |
