Effect of Small Bluntness on Formation of Görtler Vortices in a Supersonic Compression Corner Flow

The influence of small cylindrical bluntness of the leading edge of a flat plate on formation of spatial structures in a nominally two-dimensional supersonic compression corner flow at the Mach number M∞ ≈ 8 and a laminar state of the undisturbed boundary layer is studied by the method of temperatur...

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Bibliographic Details
Published in:Journal of applied mechanics and technical physics 2017-11, Vol.58 (6), p.975-989
Main Authors: Chuvakhov, P. V., Borovoy, V. Ya, Egorov, I. V., Radchenko, V. N., Olivier, H., Roghelia, A.
Format: Article
Language:English
Subjects:
Applications of Mathematics
Boundary layer
Boundary layers
Classical and Continuum Physics
Classical Mechanics
Computational fluid dynamics
Corner flow
Flat plates
Flow deflection
Flow separation
Fluid flow
Fluid- and Aerodynamics
Heat transfer coefficients
Mach number
Mathematical Modeling and Industrial Mathematics
Mechanical Engineering
Navier-Stokes equations
Oscillations
Physics
Physics and Astronomy
Plates (structural members)
Stanton number
Temperature-sensitive paints
Two dimensional flow
Velocity
Vortices
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Summary:The influence of small cylindrical bluntness of the leading edge of a flat plate on formation of spatial structures in a nominally two-dimensional supersonic compression corner flow at the Mach number M∞ ≈ 8 and a laminar state of the undisturbed boundary layer is studied by the method of temperature-sensitive paints. Streamwise vortices are found in the region of reattachment of the separated flow in a wide range of Reynolds numbers (0.15 · 10 6 –2.55 · 10 6 ) for various angles of flow deflection and plate lengths. It is demonstrated that the existence of these vortices induces spanwise oscillations of the heat transfer coefficient; the amplitude of these oscillations may reach 30%. The maximum deviations of the Stanton number reaching 80% are observed in the case with significant roughness of the leading edge of the flat plate. Both the maximum Stanton numbers in the reattachment region and the amplitude of spanwise oscillations of the Stanton number induced by streamwise vortices are found to decrease significantly in the case of small bluntness of the leading edge. Solutions of three-dimensional Navier–Stokes equations are obtained for some test conditions. The computed results are in good agreement with experimental data, which points to a significant stabilizing effect of small bluntness on the intensity of streamwise vortices.
ISSN:0021-8944
1573-8620
DOI:10.1134/S0021894417060037