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Aerospace Systems

Modeling of Shock Wave/Boundary Layer Interaction in Hypersonic Flight

nsu Aerospace Systems

Interaction of shock wave with boundary layer (SWBL) cause possible formation of recirculation zone and larger-scale zone of influence upstream and downstream of the point of the incident shock wave. These aerodynamic phenomena affect the shear and pressure forces acting on the surface, aerodynamic resistance and aerodynamic heating of propulsive systems and supersonic air vehicles.

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