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Wind Tunnel Experiments Relating to Supersonic and Hypersonic Boundary-Layer TransitionAIAA Journal, 13
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Impact of incident Mach wave on supersonic boundary layerThermophysics and Aeromechanics, 23
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INTERACTION OF MACH WAVES AND BOUNDARY LAYER AT A SUPERSONIC FLOW OVER A PLATE WITH A SHARP LEADING EDGETsagi Science Journal, 48
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Experimental study of effect of a couple of weak shock waves on boundary layer of the blunt flat plate
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Experimental study of the effects of couple weak waves on laminar-turbulent transition on attachment-line of a swept cylinder, 1770
Yu. Ermolaev, A. Kosinov, V. Kocharin, N. Semenov, A. Yatskikh (2019)
Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5Fluid Dynamics, 54
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Regimes of flow turbulization near swept wing edge in hypersonic flow
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Experimental study of weak shock waves influence on the supersonic boundary layer of the flat plate modelEPJ Web of Conferences
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The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.
Thermophysics and Aeromechanics – Springer Journals
Published: Nov 27, 2019
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