Open AccessThe experimental study of the weak shock wave action on the boundary layer of the sweep flat plate
Author(s) -
V. L. Kocharin,
А. Д. Косинов,
A. A. Yatskikh,
L. V. Afanasev,
Yu. G. Ermolaev,
Н. В. Семёнов
Publication year - 2019
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1404/1/012083
Subject(s) - anemometer , boundary layer , mach number , shock wave , mechanics , wind tunnel , oblique shock , shock (circulatory) , mach wave , flow (mathematics) , bow shock (aerodynamics) , geometry , physics , optics , materials science , mathematics , medicine , turbulence
The weak shock waves impact on the flow in the boundary layer of the sweep flat plate at Mach number 2 is studied experimentally. The model was installed at a zero angle of attack. Shock waves in the oncoming flow were generated by a two-dimensional roughness on the side wall of the wind tunnel test section. The data were obtained with a two-dimensional roughness on the wall of the wind tunnel and with a smooth wall at sweep angles (35 and 40 degrees) of the leading edge of the flat blunt plate. The measurements were carried out with a constant temperature anemometer.