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A typical example of shock wave boundary layer interaction is the flowfield past aerodynamic surfaces during control.
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The capability for CFD prediction of hypersonic shock wave laminar boundary layer interaction was assessed for a double wedge model at Mach 7.1 in air and nitrogen at 2.1 MJ/kg and 8 MJ/kg.
The capability of Computational Fluid Dynamics CFDD) software to accurately predict hypersonic shock wave laminar boundary layer interactions is examined.
Shock wave boundary layer interaction (SWBLI) is most attended research theme in the high speed flow regime for effective design of various parts of space vehicles.
Recent advances in shock wave boundary layer interaction research are reviewed in four areas: (i) understanding low frequency unsteadiness, (ii) heat transfer prediction capability, (iii) phenomena in complex (multi-shock boundary layer) interactions and (iv) flow control techniques.
Several promising flow control techniques that have more recently been applied to manipulate the shock wave/boundary layer interaction are also examined in this review.
For the tuning of the methodologies, two simple geometries have been analysed, specifically designed to study the phenomenon of shock wave boundary layer interaction: the first one is a hollow cylinder flare, for which experimental data are also available; the second one is the geometry of a test article that was designed and tested at the Italian Aerospace Research Centre.
Control of shock wave and boundary layer interaction continues to attract a lot of attention.
The aerothermodynamic loadings associated with shock wave boundary layer interactions (shock interactions) must be carefully considered in the design of hypersonic air vehicles.
This suggests that the chemical reactions themselves (cracking, depolymerization, etc)., not diffusion or boundary layer interactions common with carbonaceous biomasses, are the rate-limiting steps in the pyrolytic decomposition of waste tires.
A review of the state-of-the-knowledge of microvortex generators (MVGs) and their effect on separated shock/boundary-layer interactions is provided.
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