Transitional hypersonic flow over slender cone/flare geometries
| dc.contributor.author | Butler, Cameron S. | |
| dc.contributor.author | Laurence, Stuart J. | |
| dc.date.accessioned | 2023-09-18T17:59:26Z | |
| dc.date.available | 2023-09-18T17:59:26Z | |
| dc.date.issued | 2022-09-30 | |
| dc.description.abstract | Experiments are performed in a Mach-6 shock tunnel to examine the laminar-to-turbulent transition process associated with a sudden increase in surface angle on a slender body. A cone/flare geometry with a 5◦ frustum and compression angles ranging from 5◦ to 15◦ allow a range of mean flow configurations, spanning an attached shock-wave/boundary-layer interaction to a fully separated one; the unit Reynolds number of the flow is also varied to modify the state of incoming second-mode boundary-layer disturbances. Ultra-high-speed schlieren visualizations provide a global picture of the flow development, supplemented by high-frequency surface pressure measurements. For the 5◦ compression, the unsteady flow field is dominated by the second-mode waves, whose breakdown to turbulence is generally accelerated (compared with the straight-cone configuration) by encountering the angle change. As the compression angle is increased to induce separation, lower-frequency disturbances appear along the separated shear layer that exhibit much larger amplification rates than the incoming second-mode waves; the latter effectively freeze in amplitude downstream of the separation point before rapidly breaking down upon reattachment. The shear-layer disturbances become dominant at the largest compression angle tested. Radiation of disturbance energy to the external flow is consistently observed: this generally occurs along mean flow features (flare, separation or reattachment shocks) for the second-mode disturbances and spontaneously for the shear-layer waves. The combined application of spectral proper orthogonal decomposition and a global bispectral analysis allows the identification of important unsteady flow structures and the association of these with prominent nonlinear interactions in the various configurations. | |
| dc.description.uri | https://doi.org/10.1017/jfm.2022.769 | |
| dc.identifier | https://doi.org/10.13016/dspace/l2nj-5niw | |
| dc.identifier.citation | Change citation format Butler, C., & Laurence, S. (2022). Transitional hypersonic flow over slender cone/flare geometries. Journal of Fluid Mechanics, 949, A37. | |
| dc.identifier.uri | http://hdl.handle.net/1903/30523 | |
| dc.language.iso | en_US | |
| dc.publisher | Cambridge University Press | |
| dc.relation.isAvailableAt | A. James Clark School of Engineering | en_us |
| dc.relation.isAvailableAt | Aerospace Engineering | en_us |
| dc.relation.isAvailableAt | Digital Repository at the University of Maryland | en_us |
| dc.relation.isAvailableAt | University of Maryland (College Park, MD) | en_us |
| dc.subject | compressible boundary layers | |
| dc.subject | hypersonic flow | |
| dc.subject | transition to turbulence | |
| dc.title | Transitional hypersonic flow over slender cone/flare geometries | |
| dc.type | Article | |
| local.equitableAccessSubmission | No |