Experimental Study of the Weak Shock Wave Action on the Boundary Layer of a Plate at the Mach Number 2.5

Read more Abstract
Experimental study of the effect of a weak shock wave from the protuberance of two-dimensional roughness installed on the side wall of the test section of the wind tunnel on the supersonic boundary layer of the blunted flat plate at the Mach number 2.5 was carried out. The measurements were performed by a constant temperature hot-wire anemometer in the region of stream wise vortices generated by the shock wave from the protuberance during interaction with the flow in the vicinity of the leading edge of the model. The spectral and statistical analyses of the measured disturbances in the boundary layer were carried out. The amplitude-frequency spectra of mass flow pulsations and statistical diagrams of the measured disturbances in the supersonic part of the boundary layer were obtained.

Keywords
experiment, supersonic flow, shock wave, turbulence, boundary layer, hot-wire anemometry
Funding
The research was carried out within the framework of the Program of Fundamental Scientific Research of the state academies of sciences in 2013-2020 (project No. AAAA-A17-117030610125-7). The study was conducted at the Joint Access Center «Mechanics» of ITAM SB RAS.
УДК 532.526 

Experimental Study of the Weak Shock Wave Action on the Boundary Layer of a Plate at the Mach Number 2.5