| contributor author | Holley, Brian M. | |
| contributor author | Hardin, Larry W. | |
| contributor author | Tillman, Gregory | |
| contributor author | Lin, Ray-Sing | |
| contributor author | Joo, Jongwook | |
| date accessioned | 2022-02-04T14:14:10Z | |
| date available | 2022-02-04T14:14:10Z | |
| date copyright | 2020/01/24/ | |
| date issued | 2020 | |
| identifier issn | 0889-504X | |
| identifier other | turbo_142_2_021001.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4273242 | |
| description abstract | A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Research Center (UTRC) Acoustic Research Tunnel, an ultra-low freestream turbulence facility capable of laminar boundary layer research. Boundary layer computational fluid dynamics and stability modeling were used to provide pre-test predictions, as well as to aid in interpretation of measured results. Measurements were carried out at chord Reynolds numbers 2–3 × 106, with the model set at multiple incidence angles to establish a range of relevant leading edge pressure gradients. The combination of pressure gradient and flight Reynolds number testing on a thin airfoil has produced a unique data set relevant to propulsion system turbomachinery. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow | |
| type | Journal Paper | |
| journal volume | 142 | |
| journal issue | 2 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.4045166 | |
| page | 21001 | |
| tree | Journal of Turbomachinery:;2020:;volume( 142 ):;issue: 002 | |
| contenttype | Fulltext | |
