Calculated results(1, 2，3）Shock/shock interactions might be the most complicated flow problems observed around the hypersonic vehicles. Especially, the Type IV shock/shock interference flow induces complicated unsteady flow physics. A lot of experimental and numerical studies have been already reported. However, real flow physics are still unknown. Recently we developed the computational code for solving unsteady hypersonic 3D shock/shock interactions. The higher-resolution shock/vortex capturing method is employed. The calculated results indicate that the supersonic jet produced from the shock/shock inteference must be a key flow characteristic why the flow field is so disturbed.
Unsteady 3-D supersonic shock/turbulent-boundary-layer interaction around blunt finS.Yamamoto and N. Takasu, Numerical Study of Unsteady Shock/Boundary-Layer Interaction Induced by A Blunt Fin, Preprint of 29th AIAA Fluid Dynamics Conference, AIAA Paper 98-2815, (1998).
Satoru Yamamoto, Norinao Takasu and Hiroshi Terashima, Numerical Study of Unsteady 3D Shock/Shock Interference Flows, Proceedings of the Sixth Japan-Russia Joint Symposium on Computational Fluid Dynamics, (1998-9), 27-30.
Satoru Yamamoto and Hiroshi Terashima, Numerical Study of Unsteady 3D Hypersonic Shock Interference Flows, Computational Fluid Dynamics JOURNAL, Special Number, (2001), 766-770.
