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Transitional shock-wave/boundary-layer interactions in hypersonic flow

Transitional shock-wave/boundary-layer interactions in hypersonic flow
Transitional shock-wave/boundary-layer interactions in hypersonic flow
Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.
0022-1120
1-33
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Schuelein, E.
d6896bb8-a0de-4a22-a6d8-a4603ebb1a48
Wagner, A
333915b3-37db-4ee9-9993-462ceb0ab2ef
Willems, S
843ce874-42f5-4247-8fe4-83730657d572
Steelant, J
49000cbf-ebc7-4442-b2e6-589b664f542f
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Schuelein, E.
d6896bb8-a0de-4a22-a6d8-a4603ebb1a48
Wagner, A
333915b3-37db-4ee9-9993-462ceb0ab2ef
Willems, S
843ce874-42f5-4247-8fe4-83730657d572
Steelant, J
49000cbf-ebc7-4442-b2e6-589b664f542f

Sandham, N.D., Schuelein, E. and Wagner, A et al. (2014) Transitional shock-wave/boundary-layer interactions in hypersonic flow. Journal of Fluid Mechanics, 752, 1-33. (doi:10.1017/jfm.2014.333).

Record type: Article

Abstract

Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

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More information

Accepted/In Press date: 24 June 2014
Published date: 4 July 2014
Organisations: Aerodynamics & Flight Mechanics Group

Identifiers

Local EPrints ID: 366332
URI: http://eprints.soton.ac.uk/id/eprint/366332
ISSN: 0022-1120
PURE UUID: b9fc403a-d1b3-4627-ae26-9c6cfd324d7e
ORCID for N.D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 25 Jun 2014 10:36
Last modified: 15 Mar 2024 03:00

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Contributors

Author: N.D. Sandham ORCID iD
Author: E. Schuelein
Author: A Wagner
Author: S Willems
Author: J Steelant

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