On Determination of the Mechanism of Mach Wave / Bow-Shock Interaction

Kosinov, A. D.; Golubev, Maxim; Павлов, А. А.

doi:10.25205/2541-9447-2017-12-2-20-27

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Cited by 4 publications

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“…Typical case is when a weak shock wave falls from the side wall to the leading edge of the models [4][5][6][7][8]. Experiments have shown that in these cases the transition in the boundary layer of models is not described itself in the framework of traditional concepts.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of weak shock waves influence on the supersonic boundary layer of the flat plate model

et al. 2019

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The experimental study of the effect of weak shock waves on the supersonic boundary layer of the flat plate with a blunt leading edge (the radius of bluntness was r = 2.5 mm) with Mach number M = 2.5 and zero angle of attack was carried out. The measurements were carried out using the constant temperature anemometer. The paper presents a complex flow structure on the surface of the model. High-intensity peaks were found in the regions of the disturbed flow. Also the spectral analysis of perturbations was performed. It is found that the supersonic boundary layer on a flat plate is very sensitive to the effect of weak shock waves.

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Section: Introductionmentioning

confidence: 99%