Hypersonic Transition :

Here, our aim is to study bypass transition for flow past a sharp/blunt nosed projectile at high Mach numbers using High Accuracy Compact Methods developed by us for DNS. Charateristic based boundary conditions have been employed to take care of the three-dimensionality of the flow. The transition will be triggered selectively by introducing acoustic/entropic/vortical disturbances at the inflow in careful numerical experimentations that would simultaneously help us understand the receptivity and transition for this flow field. The formulation is able to handle problems in the Mach number range from 0.5 to 5.