TY - GEN
T1 - Hybrid RANS/LES simulation of transitional shockwave/boundary-layer interaction
AU - Tester, Bradley W.
AU - Coder, James G.
AU - Combs, Christopher S.
AU - Schmisseur, John D.
N1 - Funding Information:
supported by the U. S. Office
Funding Information:
This material is based upon research supported by the U. S. Office of Naval Research under award number N00014-15-1-2269.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - A series of delayed detached eddy simulations were run to investigate the upstream flow field of a laminar-turbulent transitional shockwave/boundary-layer interaction generated by a standing cylinder mounted to a flat plate. Both fully turbulent and transitional simulations were run, and used the one-equation, Spalart-Allmaras (SA) eddy-viscosity model with and without the amplification factor transport (AFT) transition model. The simulations showed good qualitative agreement with the experimental reference, displaying the key features. However, the simulations overpredicted the centerline surface pressure downstream of the separation shock with the transitional case showing better agreement to the experimental reference. Velocity profiles in three separate regions show similar behavior between the two cases but the transitional case exhibits stronger upstream flow in the separation region. Additionally, two regions of upstream flow are present near the flat plate surface. Centerline surface skin friction indicates the influence the upstream influence has on the boundary layer upstream of the separation shock.
AB - A series of delayed detached eddy simulations were run to investigate the upstream flow field of a laminar-turbulent transitional shockwave/boundary-layer interaction generated by a standing cylinder mounted to a flat plate. Both fully turbulent and transitional simulations were run, and used the one-equation, Spalart-Allmaras (SA) eddy-viscosity model with and without the amplification factor transport (AFT) transition model. The simulations showed good qualitative agreement with the experimental reference, displaying the key features. However, the simulations overpredicted the centerline surface pressure downstream of the separation shock with the transitional case showing better agreement to the experimental reference. Velocity profiles in three separate regions show similar behavior between the two cases but the transitional case exhibits stronger upstream flow in the separation region. Additionally, two regions of upstream flow are present near the flat plate surface. Centerline surface skin friction indicates the influence the upstream influence has on the boundary layer upstream of the separation shock.
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U2 - 10.2514/6.2018-3224
DO - 10.2514/6.2018-3224
M3 - Conference contribution
AN - SCOPUS:85051296731
SN - 9781624105531
T3 - 2018 Fluid Dynamics Conference
BT - 2018 Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 48th AIAA Fluid Dynamics Conference, 2018
Y2 - 25 June 2018 through 29 June 2018
ER -