| dc.contributor.author | Ashok Chitharenjan | |
| dc.contributor.author | Viren Menezes | |
| dc.date.accessioned | 2022-01-30T22:49:29Z | |
| dc.date.available | 2022-01-30T22:49:29Z | |
| dc.date.issued | 1/1/2021 | |
| dc.identifier.other | (ASCE)AS.1943-5525.0001203.pdf | |
| dc.identifier.uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4269688 | |
| dc.description.abstract | Shock-boundary layer interaction (SBLI) at hypersonic inlets can alter the flow pattern and impose adverse effects on engine operation if not controlled. A two-dimensional surface modification in the form of a sinusoidal wavy patch was introduced to a standard wedge-plate model in a hypersonic freestream of Mach 8.5 to test its influence on incident SBLI. Experimental and numerical comparison of flow visualization and wall pressure readings on the model with and without the wavy patch indicated a mitigating effect of the wavy patch on incident SBLI. The controlled SBLI induced significantly smaller flow separation compared with an uncontrolled case. Because of the minimally intrusive design of the wavy patch, the flow distortion/instability was notably less than that observed in the uncontrolled case. | |
| dc.publisher | ASCE | |
| dc.title | Hypersonic Incident Shock-Boundary Layer Interaction Control by Wavy Patches | |
| dc.type | Journal Paper | |
| dc.journal.volume | 34 | |
| dc.journal.issue | 1 | |
| dc.journal.title | Journal of Aerospace Engineering | |
| dc.identifier.doi | 10.1061/(ASCE)AS.1943-5525.0001203 | |
| dc.journal.fristpage | 04020092 | |
| dc.journal.lastpage | 04020092-8 | |
| dc.page | 8 | |
| dc.tree | Journal of Aerospace Engineering:;2021:;Volume ( 034 ):;issue: 001 | |
| dc.contenttype | Fulltext | |
