The experimental study of the weak shock wave action on the boundary layer of the sweep flat plate

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.

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Experimental study of heat transfer in the boundary layer of a flat plate with the impact of weak shock waves on the leading edge

10.1063/5.0028302 ◽

2020 ◽

Author(s):

V. L. Kocharin ◽

A. A. Yatskikh ◽

D. S. Prishchepova ◽

A. V. Panina ◽

Yu. G. Yermolaev ◽

...

Keyword(s):

Heat Transfer ◽

Boundary Layer ◽

Experimental Study ◽

Shock Waves ◽

Flat Plate ◽

Leading Edge ◽

Weak Shock ◽

The Impact

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Experimental study of weak shock waves influence on the supersonic boundary layer of the flat plate model

EPJ Web of Conferences ◽

10.1051/epjconf/201919600018 ◽

2019 ◽

Vol 196 ◽

pp. 00018 ◽

Cited By ~ 2

Author(s):

Vasiliy Kocharin ◽

Aleksandr Kosinov ◽

Yuriy Yermolayev ◽

Nikolay Semionov

Keyword(s):

Boundary Layer ◽

Experimental Study ◽

Shock Waves ◽

Flat Plate ◽

Leading Edge ◽

Weak Shock ◽

Supersonic Boundary Layer ◽

Complex Flow ◽

Complex Flow Structure ◽

Constant Temperature Anemometer

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.

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Experimental Study of Weak Shock Wave Propagation through a Shear Flow

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition ◽

10.2514/6.2009-1055 ◽

2009 ◽

Cited By ~ 1

Author(s):

Jae-Hyung KIM ◽

Atsushi Matsuda ◽

Akihiro Sasoh

Keyword(s):

Shock Wave ◽

Experimental Study ◽

Wave Propagation ◽

Shear Flow ◽

Weak Shock ◽

Shock Wave Propagation ◽

Weak Shock Wave

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On the interaction between shock waves and boundary layers

Mathematical Proceedings of the Cambridge Philosophical Society ◽

10.1017/s0305004100026943 ◽

1951 ◽

Vol 47 (3) ◽

pp. 545-553 ◽

Cited By ~ 14

Author(s):

K. Stewartson

Keyword(s):

Boundary Layer ◽

Shock Wave ◽

Reynolds Number ◽

Shock Waves ◽

Boundary Layers ◽

Weak Shock ◽

Boundary Layer Separation ◽

Weak Shock Wave ◽

Layer Separation ◽

Boundary Layer Equations

AbstractThe effect on the boundary-layer equations of a weak shock wave of strength ∈ has been investigated, and it is shown that ifRis the Reynolds number of the boundary layer, separation occurs when ∈ =o(R−i). The boundary-layer assumptions are then investigated and shown to be consistent. It is inferred that separation will occur if a shock wave meets a boundary and the above condition is satisfied.

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