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Experimental characterization of turbulence spots on a flat plate at Mach 6

Experimental characterization of turbulence spots on a flat plate at Mach 6
Experimental characterization of turbulence spots on a flat plate at Mach 6
Transition modelling and prediction is a critical topic at hypersonic speeds because of the physically large extent of the transition region and the impact of large variations or uncertainties in heat transfer, skin friction and other flow properties. The experimental activity presented in this paper is concerned with the intermittent region of transition, which extends from the initial breakdown of the laminar layer into turbulent ‘spots’ up to the position where the boundary layer is fully turbulent. The turbulent spots and roughness induced transition are strongly affected by compressibility and wall temperature.
To improve the quantitative understanding of these effects direct and large-eddy simulations can be performed for prescribed surface characteristics. The simulation output will provide details of boundary layer intermittency, heat transfer and skin friction for comparison with dedicated experiments conducted in an high-speed wind tunnel.
The paper will presents the results of the simulations and the first set of experiment carried out in the framework of the ATLLAS project, for a flight configuration at Mach 6. A brief critical discussion of the results will also be presented.
boundary layer transition, hypersonic, turbulent spots, dns
Passaro, A.
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Baccarella, D.
b7d62404-06cb-4017-ab7c-e2738bea2bfa
Caredda, P.
bb7cee58-05c4-464b-a033-1c476bc7a11b
Redford, J.A.
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Sandham, N.D.
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Passaro, A.
560f6034-8255-4a20-8f2a-6cf64be3e67d
Baccarella, D.
b7d62404-06cb-4017-ab7c-e2738bea2bfa
Caredda, P.
bb7cee58-05c4-464b-a033-1c476bc7a11b
Redford, J.A.
f04892d7-a782-492f-a8d7-998e9708df36
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97

Passaro, A., Baccarella, D., Caredda, P., Redford, J.A. and Sandham, N.D. (2008) Experimental characterization of turbulence spots on a flat plate at Mach 6. Sixth European Symposium on Aerothermodynamics for Space Vehicles, Versailles, France. 03 - 06 Nov 2008. 8 pp .

Record type: Conference or Workshop Item (Paper)

Abstract

Transition modelling and prediction is a critical topic at hypersonic speeds because of the physically large extent of the transition region and the impact of large variations or uncertainties in heat transfer, skin friction and other flow properties. The experimental activity presented in this paper is concerned with the intermittent region of transition, which extends from the initial breakdown of the laminar layer into turbulent ‘spots’ up to the position where the boundary layer is fully turbulent. The turbulent spots and roughness induced transition are strongly affected by compressibility and wall temperature.
To improve the quantitative understanding of these effects direct and large-eddy simulations can be performed for prescribed surface characteristics. The simulation output will provide details of boundary layer intermittency, heat transfer and skin friction for comparison with dedicated experiments conducted in an high-speed wind tunnel.
The paper will presents the results of the simulations and the first set of experiment carried out in the framework of the ATLLAS project, for a flight configuration at Mach 6. A brief critical discussion of the results will also be presented.

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Published date: November 2008
Venue - Dates: Sixth European Symposium on Aerothermodynamics for Space Vehicles, Versailles, France, 2008-11-03 - 2008-11-06
Keywords: boundary layer transition, hypersonic, turbulent spots, dns
Organisations: Aerodynamics & Flight Mechanics

Identifiers

Local EPrints ID: 64917
URI: http://eprints.soton.ac.uk/id/eprint/64917
PURE UUID: 68e90812-afbe-433b-abfd-05c9e4aa078c
ORCID for N.D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

Catalogue record

Date deposited: 23 Jan 2009
Last modified: 16 Mar 2024 03:03

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Contributors

Author: A. Passaro
Author: D. Baccarella
Author: P. Caredda
Author: J.A. Redford
Author: N.D. Sandham ORCID iD

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