Stort flight experiment after launch

9-Stort flight test

Laminar-Turbulent Transition on the STORT Flight Experiment Sebastian Willems *1, Florian Klingenberg.#1, Frank Sieb ◊1, Ali Gülhan §1, Thomas Reimer ‡2, Giuseppe Di Martino.†2, Dorian Hargarten **3, and Maximilian Zurkaulen.ƚ3   1Supersonic…
Cerruzi et al : Oxford wind tunnel experiments

10-Boundary layer experiments

Experimental investigation of boundary layer instabilities and transition on sharp and blunt cones in Oxford’s High-Density Tunnel Andrew P. Ceruzzi , andrew.ceruzzi@eng.ox.ac.uk corresponding author, Laurent M. Le Page, laurent.lepage@eng.ox.ac.uk Philipp…

11-Control of second mode

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CONTROL OF SECOND MODE INSTABILITY USING STREAK EMPLOYMENT METHOD   MUHİTTİN CELEP†, ABDELLAH HADJADJ*, MOSTAFA S. SHADLOO** †E-mail: celepm@coria.fr ,*E-mail: ahadjadj@coria.fr ,**E-mail: msshadloo@coria.fr CORIA-UMR 6614,…
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

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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…