Fig. 1: RANS simulation results for the surface heat flux on a hypersonic forebody at Mach = 6 at quiet wind tunnel test conditions, along with a cut at the forebody end providing the Mach number distribution.

15-RANS transition predictions

Comparison of RANS transition model predictions on hypersonic three-dimensional forebody configurations J.I. Cardesa1,*, G. Delattre1,** 1ONERA/DMPE, Université de Toulouse, F-31055 Toulouse, France * jcardesa@onera.fr - ** delattre@onera.fr As…

16-CONE-CYLINDER-FLARE DESIGN

,
DESIGN OF A CONE-CYLINDER-FLARE CONFIGURATION FOR HYPERSONIC BOUNDARY-LAYER STABILITY ANALYSES AND MEASUREMENTS WITH ATTACHED AND SEPARATED FLOWS Esquieu1, S. P. Schneider2, E. K. Benitez3, J-P Brazier4 1CEA, The French Alternative Energies…
Figure 1: Local wave numbers and growth rates of different eigenmodes in a cross-stream section: vortex symmetric (light blue) and antisymmetric (orange) modes, Mack mode (violet)

17-Wake of an isolated roughness

Linear stability analysis of the wake of an isolated roughness Jean-Philippe Brazier ONERA DMPE, Université de Toulouse, F-31400 Toulouse, France Jean-Philippe.Brazier@onera.fr     Keywords: Boundary layer, transition tripping,…

18-Disturbances over Blunt Cones

Nonlinear Nonmodal Disturbances over Blunt Cones at Mach 6 Paredes∗, A. Scholten†, M. Choudhari‡, F. Li‡, M. H. Carpenter‡, and M. Bailey§ ∗ National Institute of Aerospace, Hampton, VA 23666, USA † North Carolina State…
Vortex roll up in mixing layer. (a) Passive scalar, (b) Tv , (c) κ for 1 ev , (d) κ for 3 ev.

19-Thermal non-equilibrium

Thermal non-equilibrium of a high-enthalpy free shear layer during breakdown to turbulence Ali Musawi *, Neil D. Sandham * m.a.musawi@soton.ac.uk , n.sandham@soton.ac.uk * University of Southampton, Boldrewood Innovation Campus, Burgess…
Sharp cone model equipped with Kulite XCQ93 and PCB 132B39 sensors and Pitot tube equipped with Kulite XCQ93

20-Free-stream fluctuations

Free-stream fluctuations of a hypersonic conventional wind-tunnel using static and stagnation pressure sensors Sylvain Morilhat, Mathieu Lugrin, Jean-Pierre Tobeli, Nicolas Severac, Jean-Marc Luyssen, Reynald Bur ONERA DAAA, 8 rue des Vertugadins,…
Fig. 1: Skin friction obtained with transition model on the windward side of HyTRV at 2° attack angle.

21-RANS-based models predictions

Laminar-turbulent transition prediction for hypersonic vehicle with RANS-based models. Laurent MUSCAT1, Marina OLAZABAL1  1CEA CESTA, 15 Avenue des Sablières CS60001, 33116 Le Barp CEDEX, France. E-mail: laurent.muscat@cea.fr     Keywords:…
Figure 1: Outline of VKI formulation of the highlighted problem

22-High-Order Simulation

High-Order Simulation of Turbulent Hypersonic Flows Paolo Scuderi∗,1,2 , Thierry Magin1,2 , Georg May1 , Olivier Chazot1 1Aeronautics and Aerospace Department, von Karman Institute for Fluid Dynamics, Belgium 2Aéro-Thermo-Mécanique…
bow shock/particles interactions

23-particle-gas flows

Phenomenology and modeling of bow shock perturbation in particle-gas flows   AMOROSETTI Julien1, BRAEUNIG Jean-Philippe2, HEBERT David3 1, 2, 3 CEA CESTA 15 avenue des Sablières CS60001, Le Barp Cedex, 33116, France  1 julien.amorosetti@cea.fr;…

24-Simulation of Transition

  Numerical Simulation of Hypersonic transition to turbulence within the NSMB CFD solver Vos1, A. Marouf 2 and Y. Hoarau 2 1 CFS Engineering, 1 EPFL Innovation Park, Batiment A, 1015 Lausanne, Switzerland 2Université de Strasbourg, Icube…

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