درباره ما
NASA-TM-X-3302
Effect of wall suction on performance of a short annular diffuser at inlet Mach numbers up to 0.5
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:31:17Z | |
| date available | 2017-09-04T18:31:17Z | |
| date copyright | 01/01/1975 | |
| date issued | 1975 | |
| identifier other | IYHOEEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=author:%22NAVY%20-%206159DD6E273C9FCD0Facil/handle/yse/213470 | |
| description abstract | A short annular diffuser equipped with wall bleed (suction)capability was evaluated at inlet Mach numbers of 0.186 to 0.5. The diffuser had an area ratio of 4.0 and a length-to-inlet height ratio of 1.6. Test results show that the exit velocity profiles, typical of annular jet flow without suction, could be considerably flattened by application of wall suction. This improved performance was also reflected in diffuser effectiveness (static-pressure recovery) and total-pressure loss results. At the inlet Mach number of 0.5 diffuser static-pressure recovery is equal to or better than at lower inlet Mach numbers for comparable suction rates. | |
| language | English | |
| title | NASA-TM-X-3302 | num |
| title | Effect of wall suction on performance of a short annular diffuser at inlet Mach numbers up to 0.5 | en |
| type | standard | |
| page | 25 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1975 | |
| contenttype | fulltext | |
| subject keywords | AIR FLOW | |
| subject keywords | BOUNDARY LAYER CONTROL | |
| subject keywords | COMPRESSORS | |
| subject keywords | DIFFUSERS | |
| subject keywords | GAS TURBINE ENGINES | |
| subject keywords | INLET FLOW | |
| subject keywords | JET FLOW | |
| subject keywords | MACH NUMBER | |
| subject keywords | PERFORMANCE TESTS | |
| subject keywords | SUCTION | |
| subject keywords | VELOCITY DISTRIBUTION | |
| subject keywords | WALL PRESSURE |
