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Direct numerical simulation of blowing in a hypersonic boundary layer on a flat plate with slots

Direct numerical simulation of blowing in a hypersonic boundary layer on a flat plate with slots
Direct numerical simulation of blowing in a hypersonic boundary layer on a flat plate with slots
Blowing of cold fluid into a hot Mach 5 hypersonic boundary layer over a flat plate with four equally-spaced slots is analyzed through direct numerical simulation of the Navier- Stokes equations. Three different configurations are considered, namely i) a domain with simulated slots and plenum chamber, ii) a domain with only simulated slots, and iii) a domain with modelled blowing on the surface. A parametric study based on the plenum pressure is performed to investigate the effect of an increasing blowing ratio on the general flowfield structure and cooling performance. The numerical method used for the simulations consists of a 6 th -order hybrid weighted-essentially-non oscillatory/central-differencing (WENO/CD) scheme, in conjunction with an adaptive-mesh-refinement (AMR) methodology which enables accurate resolution of the flow within the plenum/slots region and inside the boundary layer. Results of two-dimensional (2D) simulations show that the plenum pressure and the simulated plenum play an important role on the structure of the mixing layer between the boundary-layer flow and the cold injected fluid, as well as on the length of the cooled region downstream of the slots. At the highest plenum pressure, the results for all the configurations show occurrence of high-amplitude oscillations of the boundary layer in the downstream region. Results of the three-dimensional (3D) simulation for the configuration including both slots and plenum chamber show transition to turbulence downstream of the slot region. Transition is induced by the breakdown of the edge vortices forming at the sides of the injection slots, and the transition front propagates downstream forming a wedge-shaped structure. Wall cooling is shown to be mostly achieved at the sides and in the wake of the slots, but as soon as the transition point is reached the wall temperature increases significantly.
American Institute of Aeronautics and Astronautics
Cerminara, Adriano
6fd11181-c852-4558-82b5-5f7eac291a3f
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97
Cerminara, Adriano
6fd11181-c852-4558-82b5-5f7eac291a3f
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Sandham, Neil
0024d8cd-c788-4811-a470-57934fbdcf97

Cerminara, Adriano, Deiterding, Ralf and Sandham, Neil (2018) Direct numerical simulation of blowing in a hypersonic boundary layer on a flat plate with slots. In AIAA AVIATION Forum: 2018 Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics. 21 pp . (doi:10.2514/6.2018-3713).

Record type: Conference or Workshop Item (Paper)

Abstract

Blowing of cold fluid into a hot Mach 5 hypersonic boundary layer over a flat plate with four equally-spaced slots is analyzed through direct numerical simulation of the Navier- Stokes equations. Three different configurations are considered, namely i) a domain with simulated slots and plenum chamber, ii) a domain with only simulated slots, and iii) a domain with modelled blowing on the surface. A parametric study based on the plenum pressure is performed to investigate the effect of an increasing blowing ratio on the general flowfield structure and cooling performance. The numerical method used for the simulations consists of a 6 th -order hybrid weighted-essentially-non oscillatory/central-differencing (WENO/CD) scheme, in conjunction with an adaptive-mesh-refinement (AMR) methodology which enables accurate resolution of the flow within the plenum/slots region and inside the boundary layer. Results of two-dimensional (2D) simulations show that the plenum pressure and the simulated plenum play an important role on the structure of the mixing layer between the boundary-layer flow and the cold injected fluid, as well as on the length of the cooled region downstream of the slots. At the highest plenum pressure, the results for all the configurations show occurrence of high-amplitude oscillations of the boundary layer in the downstream region. Results of the three-dimensional (3D) simulation for the configuration including both slots and plenum chamber show transition to turbulence downstream of the slot region. Transition is induced by the breakdown of the edge vortices forming at the sides of the injection slots, and the transition front propagates downstream forming a wedge-shaped structure. Wall cooling is shown to be mostly achieved at the sides and in the wake of the slots, but as soon as the transition point is reached the wall temperature increases significantly.

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More information

e-pub ahead of print date: 24 June 2018
Published date: 25 June 2018
Venue - Dates: AIAA Aviation Forum: 2018 Fluid Dynamics Conference, Atlanta, Georgia, 2018-06-25 - 2018-06-29

Identifiers

Local EPrints ID: 422085
URI: https://eprints.soton.ac.uk/id/eprint/422085
PURE UUID: 9e2f3efb-0761-421c-86ca-2331a2b48340
ORCID for Ralf Deiterding: ORCID iD orcid.org/0000-0003-4776-8183
ORCID for Neil Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 16 Jul 2018 16:30
Last modified: 14 Mar 2019 01:49

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