Axial component of the optimal forcing mode

12-modelling streaks effects

Hypersonic blunt bodies: modelling streaks and their effect on different transition mechanisms Caillaud 1,2, a, E. Martini1, b, G. Lehnasch1,c, and P. Jordan 1,d 1 Institut PPRIME UPR3346 CNRS, ISAE-ENSMA, Université Poitiers,86961 Futuroscope,…
Figure 1 – Instantaneous pressure pertubation featuring Mack second-mode over an adiabatic flat plate at Mach 6

13-Porous Coatings analysis

Numerical Investigation of Porous Coatings Stabilizing Capabilities on Hypersonic Boundary-Layer Transition Hammachi1,2, J. Cardesa1, E. Piot1, M. Montagnac2, H.Deniau1 1ONERA/DMPE, Université de Toulouse, F-31055 Toulouse, France 2Centre…
Stanton number highlighting transition lobes

14-Transition on BOLT forebody

Experimental hypersonic transition investigation over the BOLT forebody Authors: Loïc Sombaert1,2,†, François Nicolas1, Mathieu Lugrin1, Nicolas Severac1, Jean-Marc Luyssen1, Sylvain Morilhat1, Jean-Pierre Tobeli1, Sébastien Esquieu2,…
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:…

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