Experimental study of the action of weak shock waves on the boundary layer flow on a swept flat plate at the Mach number 2

The action of a pair of weak shock waves on a supersonic boundary layer on a swept flat plate with a bluntness radius of the leading edge equal to 2.5 mm at the Mach number 2 is experimentally studied. Transverse hot-wire measurements are performed in the boundary layer with a fixed distance of the...

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Bibliographic Details
Published in:Thermophysics and aeromechanics 2024, Vol.31 (3), p.459-464
Main Authors: Kosinov, A. D., Semionov, N. V., Shmakova, A. V., Yatskikh, A. A.
Format: Article
Language:English
Subjects:
Boundary layer flow
Flat plates
Leading edges
Mach number
Physics
Physics and Astronomy
Shock waves
Supersonic boundary layers
Sweep angle
Thermodynamics
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Summary:The action of a pair of weak shock waves on a supersonic boundary layer on a swept flat plate with a bluntness radius of the leading edge equal to 2.5 mm at the Mach number 2 is experimentally studied. Transverse hot-wire measurements are performed in the boundary layer with a fixed distance of the probe from the model surface. It is found that a change in the sweep angle of the leading edge from 35 to 45 degrees reduces the intensity of the action of the weak shock waves on the boundary layer flow. As the sweep angle of the leading edge increases to 50°, the weak shock waves no longer affect the flow in the supersonic boundary layer on the swept plate.
ISSN:0869-8643
1531-8699
DOI:10.1134/S0869864324030077