Impact of incident Mach wave on supersonic boundary
layer
A.V. Vaganov1, Yu.G. Ermolaev2, G.L. Kolosov2, A.D. Kosinov2, 3, A.V. Panina2, N.V. Semionov2, and A.A. Yatskikh2,3
1Central Aerohydrodynamic Institute, Zhukovskii, Moscow Region, Russia
2Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
3Novosibirsk State University, Novosibirsk, Russia
E-mail: kosinov@itam.nsc.ru
Keywords: supersonic velocities, experimental studies, wind tunnel, flat plate, sharp and blunt leading edges, boundary layer, hot-wire anemometry
Pages: 43–48
Abstract
Results of an
experimental study of the excitation of high-intensity disturbances by a weak
external shock wave in laminar boundary layer on flat-plate models with sharp
and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker
in turbulent boundary layer on the wall of wind-tunnel test section in the free
stream is shown to have the form of an
N-wave. It is found that, on the blunted plate, the intensity of pulsations
produced by weak external shock waves in boundary layer several times exceeds
the intensity of pulsations produced in boundary layer on the model with a
sharp leading edge.
DOI: 10.1134/S0869864316010054
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