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- W2186263784 abstract "Currently, the mechanisms leading to hypersonic boundary layer transition are still poorly understood. The transition in the boundary layer depends on the receptivity process, which is the process of environmental disturbances initially entering the boundary layers and generating disturbance waves. The receptivity of hypersonic boundary layers to free stream disturbances is altered considerably by the presence of bow shocks in hypersonic flow fields and by the entropy layers created by the blunt nose. This paper conducts a numerical simulation study of the receptivity to freestream acoustic disturban& waves for Mach 7.99 axisymmetric flow over a io half-angle blunt cone, and compares the numerical results with experimental results by Stetson et al. (1984) and with those obtained from linear stability. Both steady and unsteady flow solutions of the receptivity problem are obtained by computing the full Navier-Stokes equations using a high-order accurate shock-fitting finite difference scheme, which can accurately account for the effects of bow-sho&/free-streamsound interactions on the receptivity process. In addition, a normal-mode linear stability analysis is also used to study the stability and receptivity properties of the boundary layer affected by the entropy layer. The main focus of this study is on the excitation of the second mode waves in the receptivity process in the presense of freestream acoustic waves. One of the major findings of this study is that, for the case of receptivity to fast freestream acoustic waves with a blunt nose, the second mode waves are not excited in the early region dong the cone surface where the second modes are pre dicted to be unstable by the linear stability analysis. It is shown that the delay of the second mode excitation is due to the unique stability characteristics of the current flow which are affected by the entropy layer produced by the nose bluntness. The understanding of such receptivity processes may lead to a better understanding of nose bluntness effects on hypersonic boundary layer transition and the accuracy of the LST analysis." @default.
- W2186263784 created "2016-06-24" @default.
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- W2186263784 date "2002-01-01" @default.
- W2186263784 modified "2023-09-27" @default.
- W2186263784 title "RECEPTIVITY AND LINEAR STABILITY OF STETSON'S MACH 8 BLUNT CONE STABILITY EXPERIMENTS" @default.
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