Computational Analysis of the Transonic Flow Field of Two-Dimensional Minimum Length NozzlesSource: Journal of Fluids Engineering:;1991:;volume( 113 ):;issue: 003::page 479DOI: 10.1115/1.2909521Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The method of characteristics is used to generate supersonic wall contours for two-dimensional, straight sonic line (SSL) and curved sonic line (CSL) minimum length nozzles for exit Mach numbers of two, four and six. These contours are combined with subsonic inlets to determine the influence of the inlet geometry on the sonic-line shape, its location, and on the supersonic flow field. A modified version of the VNAP2 code is used to compute the inviscid and laminar flow fields for Reynolds numbers of 1,170, 11,700, and 23,400. Supersonic flow field phenomena, including boundary-layer separation and oblique shock waves, are observed to be a result of the inlet geometry. The sonic-line assumptions made for the SSL prove to be superior to those of the CSL.
keyword(s): Nozzles , Transonic flow , Supersonic flow , Geometry , Shapes , Mach number , Separation (Technology) , Shock waves , Laminar flow , Reynolds number AND Boundary layers ,
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| contributor author | B. M. Argrow | |
| contributor author | G. Emanuel | |
| date accessioned | 2017-05-08T23:35:48Z | |
| date available | 2017-05-08T23:35:48Z | |
| date copyright | September, 1991 | |
| date issued | 1991 | |
| identifier issn | 0098-2202 | |
| identifier other | JFEGA4-27061#479_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/108718 | |
| description abstract | The method of characteristics is used to generate supersonic wall contours for two-dimensional, straight sonic line (SSL) and curved sonic line (CSL) minimum length nozzles for exit Mach numbers of two, four and six. These contours are combined with subsonic inlets to determine the influence of the inlet geometry on the sonic-line shape, its location, and on the supersonic flow field. A modified version of the VNAP2 code is used to compute the inviscid and laminar flow fields for Reynolds numbers of 1,170, 11,700, and 23,400. Supersonic flow field phenomena, including boundary-layer separation and oblique shock waves, are observed to be a result of the inlet geometry. The sonic-line assumptions made for the SSL prove to be superior to those of the CSL. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Computational Analysis of the Transonic Flow Field of Two-Dimensional Minimum Length Nozzles | |
| type | Journal Paper | |
| journal volume | 113 | |
| journal issue | 3 | |
| journal title | Journal of Fluids Engineering | |
| identifier doi | 10.1115/1.2909521 | |
| journal fristpage | 479 | |
| journal lastpage | 488 | |
| identifier eissn | 1528-901X | |
| keywords | Nozzles | |
| keywords | Transonic flow | |
| keywords | Supersonic flow | |
| keywords | Geometry | |
| keywords | Shapes | |
| keywords | Mach number | |
| keywords | Separation (Technology) | |
| keywords | Shock waves | |
| keywords | Laminar flow | |
| keywords | Reynolds number AND Boundary layers | |
| tree | Journal of Fluids Engineering:;1991:;volume( 113 ):;issue: 003 | |
| contenttype | Fulltext |