Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation
Two-dimensional mapping of the velocity distribution for a hypersonic leading-edge separation flowfield generated by a "tick" shaped geometry is presented for the first time. Discrete measurements of two velocity components were acquired at a flow condition having a total specific enthalpy...
| Main Authors: | , , , |
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| Format: | Journal article |
| Language: | English |
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AIP Publishing
2020
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| _version_ | 1826310965395718144 |
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| author | Le Page, LM Barrett, M O'Byrne, S Gai, SL |
| author_facet | Le Page, LM Barrett, M O'Byrne, S Gai, SL |
| author_sort | Le Page, LM |
| collection | OXFORD |
| description | Two-dimensional mapping of the velocity distribution for a hypersonic leading-edge separation flowfield generated by a "tick" shaped geometry is presented for the first time. Discrete measurements of two velocity components were acquired at a flow condition having a total specific enthalpy of 3.8 MJ/kg by imaging nitric oxide fluorescence over numerous runs of the hypersonic tunnel at the Australian Defence Force Academy (T-ADFA). The measured freestream velocity distribution exhibited some non-uniformity, which is hypothesized to originate from images acquired using a set of ultraviolet specific mirrors mounted on the shock tunnel deflecting under load during a run of the facility, slightly changing the laser sheet orientation. The flow separation point was measured to occur at 1.4 ± 0.2 mm from the model leading edge, based on the origin of the free shear layer emanating from the expansion surface. Reattachment of this free shear layer on the compression surface occurred at 59.0 ± 0.2 mm from the model vertex. Recirculating the flow bound by the separation and reattachment points contained supersonic reverse flow and areas of subsonic flow aligned with the location of three identified counter-rotating vortices. A comparison of the recirculation flow streamline plots with those computed using Navier-Stokes and direct simulation Monte Carlo (DSMC) codes showed differences in flow structures. At a flow time close to that produced by the facility, flow structures generated by the DSMC solution were seen to agree more favorably with the experiment than those generated by the Navier-Stokes solver due to its ability to better characterize separation by modeling the strong viscous interactions and rarefaction at the leading edge. The primary reason for this is that the no-slip condition used in the Navier-Stokes solution predicts a closer separation point to the leading edge and structures when compared to the DSMC solution, which affects surface shear stress and heat flux, leading to a difference in flow structures downstream of the separation. |
| first_indexed | 2024-03-07T08:01:22Z |
| format | Journal article |
| id | oxford-uuid:faa4c513-c4ac-4d90-b7fa-a9ac22d8067a |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-07T08:01:22Z |
| publishDate | 2020 |
| publisher | AIP Publishing |
| record_format | dspace |
| spelling | oxford-uuid:faa4c513-c4ac-4d90-b7fa-a9ac22d8067a2023-09-22T11:58:59ZLaser-induced fluorescence velocimetry for a hypersonic leading-edge separationJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:faa4c513-c4ac-4d90-b7fa-a9ac22d8067aEnglishSymplectic ElementsAIP Publishing2020Le Page, LMBarrett, MO'Byrne, SGai, SLTwo-dimensional mapping of the velocity distribution for a hypersonic leading-edge separation flowfield generated by a "tick" shaped geometry is presented for the first time. Discrete measurements of two velocity components were acquired at a flow condition having a total specific enthalpy of 3.8 MJ/kg by imaging nitric oxide fluorescence over numerous runs of the hypersonic tunnel at the Australian Defence Force Academy (T-ADFA). The measured freestream velocity distribution exhibited some non-uniformity, which is hypothesized to originate from images acquired using a set of ultraviolet specific mirrors mounted on the shock tunnel deflecting under load during a run of the facility, slightly changing the laser sheet orientation. The flow separation point was measured to occur at 1.4 ± 0.2 mm from the model leading edge, based on the origin of the free shear layer emanating from the expansion surface. Reattachment of this free shear layer on the compression surface occurred at 59.0 ± 0.2 mm from the model vertex. Recirculating the flow bound by the separation and reattachment points contained supersonic reverse flow and areas of subsonic flow aligned with the location of three identified counter-rotating vortices. A comparison of the recirculation flow streamline plots with those computed using Navier-Stokes and direct simulation Monte Carlo (DSMC) codes showed differences in flow structures. At a flow time close to that produced by the facility, flow structures generated by the DSMC solution were seen to agree more favorably with the experiment than those generated by the Navier-Stokes solver due to its ability to better characterize separation by modeling the strong viscous interactions and rarefaction at the leading edge. The primary reason for this is that the no-slip condition used in the Navier-Stokes solution predicts a closer separation point to the leading edge and structures when compared to the DSMC solution, which affects surface shear stress and heat flux, leading to a difference in flow structures downstream of the separation. |
| spellingShingle | Le Page, LM Barrett, M O'Byrne, S Gai, SL Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title | Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title_full | Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title_fullStr | Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title_full_unstemmed | Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title_short | Laser-induced fluorescence velocimetry for a hypersonic leading-edge separation |
| title_sort | laser induced fluorescence velocimetry for a hypersonic leading edge separation |
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