On the accuracy of numerical simulation of the boundary layer separation on a finite-width wedge

Bosnyakov, S. M.; Babulin, A. A.; Власенко, В. В.; Engulatova, M. F.; Matyash, S. V.; Mikhaylov, Sergey

doi:10.1134/s2070048216030042

Cited by 3 publications

(1 citation statement)

References 7 publications

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“…In rocket propulsion systems, these effects affect the flow in the nozzles of supersonic engines [6]. In a number of experimental studies of flows of this class [3,4] and works on numerical modeling [1,2,6,7], it was found that in the separation zone the pressure and the heat transfer coefficient increase sharply. Generally, numerical simulation reflects the main features of the studied flows correctly, however the calculated values in developed separation zones generated by strong shock waves differ from experimental ones [5].…”

Section: Introductionmentioning

confidence: 99%

Visualization of the interaction region of an oblique shock wave with a boundary layer by the radiation of a nanosecond surface sliding discharge

Mursenkova¹,

Sazonov²,

Liao³

et al. 2019

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The spatial structure of radiation of a surface sliding discharge with a duration of ~ 300 ns (plasma sheet) in inhomogeneous supersonic air flows including oblique shock wave in a discharge chamber of shock tube was experimentally investigated. The flows were created behind plane shock waves with Mach numbers 2.8-4.2; flow Mach numbers were 1.30-1.60. The flow in the discharge chamber included an oblique shock wave generated by the interaction of a supersonic flow with a small obstacle, and then reflected from the upper wall of the discharge chamber. In this case, the shock wave interacted with the boundary layer of the supersonic flow, which formed on the streamlined wall. A surface sliding discharge with a length of 100 mm and 30 mm wide was initiated on a streamlined surface at a certain moment in time. The discharge current, emission spectra, and spatial characteristics of the radiation under various conditions of discharge initiation were obtained and analyzed in experiments. The time dependence of geometry of the discharge glow region was obtained by digital processing of discharge images in flows. CFD simulation was performed to determine the shock-wave structure of the flow in the channel with an obstacle under experimental conditions. The comparison of experimental data with the results of numerical calculation of the supersonic flow field was done. It was shown that the spatial distribution of radiation from a surface sliding discharge visualizes the low density areas and the separation zone formed under the interaction of an oblique shock wave with a boundary layer.

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