Experimental study of weak shock waves influence on the supersonic boundary layer of the flat plate model
1 Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, 630090 Novosibirsk, Russia
2 Novosibirsk State University, Novosibirsk, Russia
* Corresponding author: email@example.com
Published online: 14 January 2019
The experimental study of the effect of weak shock waves on the supersonic boundary layer of the flat plate with a blunt leading edge (the radius of bluntness was r = 2.5 mm) with Mach number M = 2.5 and zero angle of attack was carried out. The measurements were carried out using the constant temperature anemometer. The paper presents a complex flow structure on the surface of the model. High-intensity peaks were found in the regions of the disturbed flow. Also the spectral analysis of perturbations was performed. It is found that the supersonic boundary layer on a flat plate is very sensitive to the effect of weak shock waves.
© The Authors, published by EDP Sciences, 2019
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