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Oblique shock
About: Oblique shock is a research topic. Over the lifetime, 6551 publications have been published within this topic receiving 119823 citations.
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TL;DR: Oblique shock-wave reflections in nitrogen for perfect and imperfect gases were investigated interferometrically in a 10x 18-cm shock tube as mentioned in this paper, and the results showed that the available numerical techniques will have to be modified or new approaches developed before acceptable agreement can be obtained between actual and numerical experiments.
Abstract: Oblique shock-wave reflections in nitrogen for perfect and imperfect gases were investigated interferometrically in a 10x 18-cm shock tube. Comparisons are made with numerical experiments conducted by two different groups on regular and single-Mach reflections. Even though the analyses are for inviscid flows, the sidewall boundary-layer effects in the experiments are negligible, and the features of the calculated and actual inviscid flows are compared readily. It is found that the available numerical techniques will have to be modified or new approaches developed before acceptable agreement can be obtained between actual and numerical experiments. The very accurate interferometric data will provide a basis for comparison with future numerical methods, which also should include the two remaining cases of complexand double-Mach reflections as a test of their accuracy and applicability.
41 citations
TL;DR: In this article, an experimental study of the interaction between streamwise vortices and two-dimensional oblique shock waves has been conducted at Mach 2.5, where the experiments involved positioning an instrumented 2D wedge downstream of a semispan wing so that the trailing tip vortex from the wing interacted with the oblique wave formed over the wedge surface.
Abstract: An experimental study of the interaction between streamwise vortices and two-dimensional oblique shock waves has been conducted at Mach 2.5. The experiments involved positioning an instrumented two-dimensional wedge downstream of a semispan wing so that the trailing tip vortex from the wing interacted with the oblique shock wave formed over the wedge surface. The experiments were designed to simulate interaction of streamwise vortices with shock waves formed over aerodynamic surfaces or in supersonic inlets. The influence of oblique shock wave intensity on this inherently three-dimensional interaction was examined for vortices of variable strength. Results indicate that the interaction of a moderate strength vortex with an oblique shock wave can lead to the formation of a steady separated shock structure upstream of the oblique shock front. A significant expansion of the vortex core is observed in these cases, and the scale of the structure increases with shock wave intensity. In some instances the separated shock structure continues through the oblique shock front to strike the shock-generating wedge forming a three-dimensional shock-wave/boundary-layer interaction. The experiments indicate that significant distortion of streamwise vortices can be precipitated by oblique shock fronts with supersonic downstream conditions.
41 citations
TL;DR: In this paper, the location and size of the Mach disk are governed by the appearance of a triple-point shock configuration and the condition that the central core flow will reach a state of choking at a throat.
Abstract: The flowfield associated with the underexpanded axisymmetric nozzle freejet flow including the appearance of a Mach disk has been studied. It is shown that the location and size of the Mach disk are governed by the appearance of a triple-point shock configuration and the condition that the central core flow will reach a state of 'choking at a throat'. It is recognized that coalescence of waves requires special attention and the reflected wave, as well as the vorticity generated from these wave interactions, have to be taken accurately into account. The theoretical results obtained agreed well with the experimental data.
41 citations
TL;DR: In this article, the effect of upstream waves on the local shock angle, the control of ion reflection and sharp field gradients by upstream waves, the interaction of cold reflected ion beams and upstream waves; the growth of upstream wave into large amplitude structures at the shock transition; the role of energetic particles.
40 citations
40 citations