On the response of shock-induced separation bubble to small amplitude disturbances
On the response of shock-induced separation bubble to small amplitude disturbances
Numerical simulations of an oblique shock interacting with a compressible laminar boundary layer are reported. The Mach number ranges from 2 to 6.85, while the Reynolds number based on the distance to the impingement location is fixed at 3 × 10^5. All the simulations are carried out with a constant wall temperature, equal to the adiabatic recovery temperature. At higher shock strength the evolved separation bubbles are taller and are biased towards the upstream side of the impingement location with an asymmetrical structure. Existing similarity scalings for the bubble length need to be modified for the high Mach number range. Introduction of small amplitude disturbances upstream of the separation bubble resulted in the growth of organised streamwise structures downstream of the bubble.
shock/boundary-layer interactions, transition to turbulence
1495-1498
Krishnan, L.
4eb5cfc3-d3e2-474d-a63b-e1f80de54bf6
Yao, Y.
686239b3-5065-414b-9056-72dffa43116c
Sandham, N.D.
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Roberts, G.T.
deaf59ac-e4ee-4fc2-accf-df0639d39368
2005
Krishnan, L.
4eb5cfc3-d3e2-474d-a63b-e1f80de54bf6
Yao, Y.
686239b3-5065-414b-9056-72dffa43116c
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Roberts, G.T.
deaf59ac-e4ee-4fc2-accf-df0639d39368
Krishnan, L., Yao, Y., Sandham, N.D. and Roberts, G.T.
(2005)
On the response of shock-induced separation bubble to small amplitude disturbances.
Modern Physics Letters B, 19 (28-29), .
(doi:10.1142/S0217984905009742).
Abstract
Numerical simulations of an oblique shock interacting with a compressible laminar boundary layer are reported. The Mach number ranges from 2 to 6.85, while the Reynolds number based on the distance to the impingement location is fixed at 3 × 10^5. All the simulations are carried out with a constant wall temperature, equal to the adiabatic recovery temperature. At higher shock strength the evolved separation bubbles are taller and are biased towards the upstream side of the impingement location with an asymmetrical structure. Existing similarity scalings for the bubble length need to be modified for the high Mach number range. Introduction of small amplitude disturbances upstream of the separation bubble resulted in the growth of organised streamwise structures downstream of the bubble.
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Published date: 2005
Keywords:
shock/boundary-layer interactions, transition to turbulence
Organisations:
Aerodynamics & Flight Mechanics
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Local EPrints ID: 23779
URI: http://eprints.soton.ac.uk/id/eprint/23779
ISSN: 0217-9849
PURE UUID: 9c7f2214-42a8-447a-9bbb-b60385d4e77e
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Date deposited: 20 Mar 2006
Last modified: 16 Mar 2024 03:03
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Author:
L. Krishnan
Author:
Y. Yao
Author:
N.D. Sandham
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