Abstract
This paper presents the numerical simulations of transient flow under the interaction between freestream hotspot perturbations and bow-shock on Purdue’s blunt compression cone with the effects of different nosebluntness and various freestream Mach numbers. The basic flow conditions are referring to Boeing/AFOSR Mach-6 Quiet tunnel (BAM6QT) at Purdue University. The simulations in this paper consist of two cases of different nose-radii and two cases of different freestream Mach numbers. The detailed analysis of the receptivity mechanisms is carried out with linear stability theory (LST). The simulation results agree well with LST analyses. The parametric study is performed by the comparisons of the simulation results with the Mach-6 results that have been carried out previously. The study shows the sharper cone destabilizes the boundary layer, and the higher freestream Mach number stabilizes it. The receptivity mechanisms under both effects are shown to be the same: the second mode instability is induced by the fast acoustic waves behind the shock in the nose region.
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