Diffraction phenomena upon incidence of a pair of weak shock waves on the leading edge of a flat plate model at supersonic freestream velocities

Results are presented of hot-wire measurements of the freestream and the boundary layer on a flat plate with a blunt leading edge in the presence of an N-wave as a disturbance source. Based on the measurements, estimates of cross-correlation characteristics were obtained. From the distribution of mutual phases, conclusions were drawn regarding the presence of diffraction phenomena of freestream pulsations. It is shown that, in contrast to the case of a sharp leading edge, the presence of diffraction phenomena cannot be reliably determined for a blunt leading edge.

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Publication Details

Journal
Thermophysics and Aeromechanics
Published
2026-06-09
DOI
https://doi.org/10.1134/s0869864325050038
Primary Topic
Computational Fluid Dynamics and Aerodynamics
Type
article
Field-Weighted Citation Impact
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article

Diffraction phenomena upon incidence of a pair of weak shock waves on the leading edge of a flat plate model at supersonic freestream velocities

Yu. G. Ermolaev, Е.Д. Карлова, A. D. Kosinov, L. V. Afanasev et al.
Thermophysics and Aeromechanics
Computational Fluid Dynamics and Aerodynamics
article

Diffraction phenomena upon incidence of a pair of weak shock waves on the leading edge of a flat plate model at supersonic freestream velocities

Yu. G. Ermolaev, Е.Д. Карлова, A. D. Kosinov, L. V. Afanasev, A. A. Yatskikh
article en

Abstract

Results are presented of hot-wire measurements of the freestream and the boundary layer on a flat plate with a blunt leading edge in the presence of an N-wave as a disturbance source. Based on the measurements, estimates of cross-correlation characteristics were obtained. From the distribution of mutual phases, conclusions were drawn regarding the presence of diffraction phenomena of freestream pulsations. It is shown that, in contrast to the case of a sharp leading edge, the presence of diffraction phenomena cannot be reliably determined for a blunt leading edge.

Thermophysics and AeromechanicsVol. 32(5)
Institute of Theoretical and Applied Mechanics (RU)
Openalex Percentile: Top 7%
Computational Fluid Dynamics and Aerodynamics
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