Dependence Between Shock and Separation Bubble in a Shock Wave Boundary Layer Interaction
We present experimental results obtained in a turbulent boundary layer at a Mach number of 2.3 impinged by an oblique shock wave. Strong unsteadinesses are developed in the interaction, involving several frequency ranges which can extend over two orders of magnitude. In this paper, attention is focused on the links between the low frequencies shock motions and the separation bubble. An interpretation based on a simple scheme of the longitudinal evolution of the instantaneous pressure is proposed. As it is mainly based on the pressure signals properties inside the region of the shock oscillation, it may be expected that it will be still relevant for different configurations of shock induced separation as compression ramp, blunt bodies or over expanded nozzles.
KeywordsShock wave Boundary layer separation Unsteadiness
Part of this work was carried out with the support of the Research Pole CNES/ONERA Aérodynamique des Tuyères et Arrière-Corps (ATAC) and with a grant of the European STREP UFAST (DGXII). Their support is gratefully acknowledged. Comments of Dr. J.P. Dussauge are also gratefully acknowledged.
- 3.A. Nguyen, H. Deniau, S. Girard, T.A. de Roquefort, in 38th AIAA Joint Propulsion Conference, Indianapolis, AIAA Paper, 02-4001, Indianapolis, Indiana, USA (2002)Google Scholar
- 4.C. Haddad, Instationnarités, mouvements d'onde de choc et tourbillons à grande échelles dans une interaction onde de choc/couche limite avec décollement. Thèse de doctorat, Université de Provence Aix-Marseille I (2005)Google Scholar
- 8.B. Ganapathisubramani, N. Clemens, D. Dolling, in 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 8–11 January (2007)Google Scholar