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Numerical study of oblique shock-wave/boundary-layer interaction considering sidewall effects

Numerical study of oblique shock-wave/boundary-layer interaction considering sidewall effects
Numerical study of oblique shock-wave/boundary-layer interaction considering sidewall effects
Large-eddy simulations are conducted to uncover physical aspects of sidewall-induced three-dimensionality for a moderately separated oblique shock-wave/boundary-layer interaction (SWBLI) at M=2.7. Simulations are run for three different aspect ratios of the interaction zone. The swept SWBLI on the sidewalls and the corner flow behaviour are investigated, along with the main oblique SWBLI on the bottom wall. As the aspect ratio decreases to unity, the separation and reattachment points on the central plane are observed to move upstream simultaneously, while the bubble length initially increases and then stabilizes to a length 30 % larger than for the infinite-span quasi-two-dimensional case. A distorted incident shock and a three-dimensional (3D) bottom-wall separation pattern are observed, with a patch of attached flow between the central and corner separations. The 3D flow structure is found to be induced by the swept SWBLI formed on the sidewalls. The location of the termination point of the incident shock near the sidewall is limited by a sweepback effect, allowing the definition of a penetration Mach number Mp that is shown to correlate well with the spanwise extent of the core flow. The structure and strength of the incident shock are modified significantly by the swept SWBLI on the sidewalls, along with a compression wave upstream and a secondary sidewall shock downstream, leading to a highly 3D pressure field in the main flow above the main SWBLI on the bottom wall. The reflection of the swept SWBLI from the bottom wall leads to a corner compression wave and strong transverse flow close to the bottom wall. A physical model based on the quasi-conical structure of the swept SWBLI on the sidewall is proposed to estimate the 3D SWBLI pattern on the bottom wall, in which the swept SWBLI features and the aspect ratio of the interaction zone are considered to be the critical factors
boundary layer separation, high-speed flow, shock waves
0022-1120
526-561
Wang, Bo
d0ff5cee-f10c-4312-bbdc-c1330fd57a46
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97
Hu, Zhiwei
dd985844-1e6b-44ba-9e1d-fa57c6c88d65
Liu, Weidong
3f74bc18-9bfe-43ae-8dc4-c1d06850eb65
Wang, Bo
d0ff5cee-f10c-4312-bbdc-c1330fd57a46
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97
Hu, Zhiwei
dd985844-1e6b-44ba-9e1d-fa57c6c88d65
Liu, Weidong
3f74bc18-9bfe-43ae-8dc4-c1d06850eb65

Wang, Bo, Sandham, Neil D., Hu, Zhiwei and Liu, Weidong (2015) Numerical study of oblique shock-wave/boundary-layer interaction considering sidewall effects. Journal of Fluid Mechanics, 767, 526-561. (doi:10.1017/jfm.2015.58).

Record type: Article

Abstract

Large-eddy simulations are conducted to uncover physical aspects of sidewall-induced three-dimensionality for a moderately separated oblique shock-wave/boundary-layer interaction (SWBLI) at M=2.7. Simulations are run for three different aspect ratios of the interaction zone. The swept SWBLI on the sidewalls and the corner flow behaviour are investigated, along with the main oblique SWBLI on the bottom wall. As the aspect ratio decreases to unity, the separation and reattachment points on the central plane are observed to move upstream simultaneously, while the bubble length initially increases and then stabilizes to a length 30 % larger than for the infinite-span quasi-two-dimensional case. A distorted incident shock and a three-dimensional (3D) bottom-wall separation pattern are observed, with a patch of attached flow between the central and corner separations. The 3D flow structure is found to be induced by the swept SWBLI formed on the sidewalls. The location of the termination point of the incident shock near the sidewall is limited by a sweepback effect, allowing the definition of a penetration Mach number Mp that is shown to correlate well with the spanwise extent of the core flow. The structure and strength of the incident shock are modified significantly by the swept SWBLI on the sidewalls, along with a compression wave upstream and a secondary sidewall shock downstream, leading to a highly 3D pressure field in the main flow above the main SWBLI on the bottom wall. The reflection of the swept SWBLI from the bottom wall leads to a corner compression wave and strong transverse flow close to the bottom wall. A physical model based on the quasi-conical structure of the swept SWBLI on the sidewall is proposed to estimate the 3D SWBLI pattern on the bottom wall, in which the swept SWBLI features and the aspect ratio of the interaction zone are considered to be the critical factors

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Accepted/In Press date: 23 January 2015
e-pub ahead of print date: 20 February 2015
Published date: 25 March 2015
Keywords: boundary layer separation, high-speed flow, shock waves
Organisations: Aerodynamics & Flight Mechanics Group

Identifiers

Local EPrints ID: 374582
URI: http://eprints.soton.ac.uk/id/eprint/374582
ISSN: 0022-1120
PURE UUID: a195b449-0743-4629-8e84-05a9e22be5b6
ORCID for Neil D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 23 Feb 2015 09:57
Last modified: 15 Mar 2024 03:00

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Contributors

Author: Bo Wang
Author: Neil D. Sandham ORCID iD
Author: Zhiwei Hu
Author: Weidong Liu

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