Hostname: page-component-745bb68f8f-b95js Total loading time: 0 Render date: 2025-02-02T06:56:05.675Z Has data issue: false hasContentIssue false
  • English
  • Français

Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction

Published online by Cambridge University Press:  20 April 2006

Ching-Mao Hung  and
Pieter G. Buning
Ching-Mao Hung
Affiliation:
Computational Fluid Dynamics Branch, NASA Ames Research Center, Moffett Field, California
Pieter G. Buning
Affiliation:
Computational Fluid Dynamics Branch, NASA Ames Research Center, Moffett Field, California
Get access Rights & Permissions [Opens in a new window]

Abstract

The Reynolds-averaged Navier–Stokes equations are solved numerically for supersonic flow over a blunt fin mounted on a flat plate. The fin shock causes the boundary layer to separate, which results in a complicated, three-dimensional shock-wave and boundary-layer interaction. The computed results are in good agreement with the mean static pressure measured on the fin and the flat plate. The main features, such as peak pressure on the fin leading edge and a double peak on the plate, are predicted well. The role of the horseshoe vortex is discussed. This vortex leads to the development of high-speed flow and, hence, low-pressure regions on the fin and the plate. Different thicknesses of the incoming boundary layer have been studied. Varying the thicknesses by an order of magnitude shows that the size of the horseshoe vortex and, therefore, the spatial extent of the interaction are dominated by inviscid flow and only weakly dependent on the Reynolds number. Coloured graphics are used to show details of the interaction flow field.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 154 , May 1985 , pp. 163 - 185
Copyright
© 1985 Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Baldwin, B. S. & Lomax, H. 1978 Thin-layer approximation and algebraic model for separated turbulent flows. AIAA paper 78-257.
Chapman, D. R., Kuehn, D. M. & Larson, H. K. 1958 Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition. NACA Rep. 1356.Google Scholar
Degani, D. & Schiff, L. B. 1983 Computation of supersonic viscous flows around pointed bodies at large incidence. AIAA paper 83-0034.
Dolling, D. S. & Bogdonoff, S. M. 1981 An experimental investigation of the unsteady behavior of blunt fin-induced shock wave turbulent boundary layer interaction. AIAA paper 81-1287.
Dolling, D. S. & Bogdonoff, S. M. 1982 Blunt fin-induced shock wave/turbulent boundary layer interaction. AIAA J. 20, 1674–1680.Google Scholar
Dolling, D. S., Cosad, C. D. & Bogdonoff, S. M. 1979 An examination of blunt fin-induced shock wave turbulent boundary layer interaction. AIAA paper 79-0068.
Edney, B. 1968 Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Aeronautical Research Institute of Sweden, Stockholm, Sweden, Rep. 115.Google Scholar
Hayakawa, K., Smits, A. J. & Bogdonoff, S. M. 1984 Hot-wire investigation of an unseparated shock-wave/turbulent boundary-layer interaction. AIAA J. 22, 579–585.Google Scholar
Horstman, C. C., Settles, G. S., Vas, I. E., Bogdonoff, S. M. & Hung, C. M. 1977 Reynolds number effects of shock-wave turbulent boundary-layer interactions. AIAA J. 15, 1152–1158.Google Scholar
Hung, C. M. & Kordulla, W. 1984 A time-split finite-volume algorithm for three-dimensional flowfield simulation. AIAA J. 22, 1564–1572.Google Scholar
Hung, C. M. & Kurasaki, S. S. 1980 Thin-layer approximation for three-dimensional supersonic corner flows. AIAA J. 18, 1544–1546.Google Scholar
Hung, C. M. & MacCormack, R. W. 1979 Numerical solution of three-dimensional shock wave and boundary layer interaction. AIAA J. 16, 1090–1096.Google Scholar
Kaufman, L. G., Korkegi, R. H. & Morton, L. C. 1972 Shock impingement caused by boundary layer separation ahead of blunt fin. ARL 72-0118, 1972, Wright-Patterson Air Force Base, Ohio.
Maccormack, R. W. 1982 A numerical method for solving the equations of compressible viscous flow. AIAA J. 20, 1275–1281.Google Scholar
Nebbleling, C. & Bannink, W. J. 1978 Experimental investigation of the supersonic flow past a slender cone at high incidence. J. Fluid Mech. 87, 475–496.Google Scholar
Norman, R. S. 1972 On obstacle generated secondary flows in laminar boundary layers and transition to turbulence. Ph.D. thesis, Illinois Institute of Technology.
Ozcan, K. 1982 An experimental investigation of three-dimensional boundary layer separation in supersonic flow past a circular cylinder on a flat plate. Ph.D. thesis, University of California, Berkeley.
Price, A. E. & Stalling, R. L. 1967 Investigation of turbulent separated flows in the vicinity of fin type protuberances at supersonic Mach number. NASA TN D-3804.
Rubin, S. G. 1966 Incompressible flow along a corner. J. Fluid Mech. 26, 99–110.Google Scholar
Sedney, R. & Kitchens, C. W. 1975 The structure of three-dimensional separated flows in obstacle, boundary-layer interactions. Flow Separation, AGARD Cp-168, paper 37.
Strang, G. 1968 On the construction and comparison of difference schemes. SIAM J. Numer. Anal. 5, 506–517.Google Scholar
Teng, H. Y. & Settles, G. S. 1982 Cylindrical and conical upstream influence regimes of 3D shock/turbulent layer interactions. AIAA paper 82-0987.
Voltenko, D. M., Zubkov, A. I. & Panov, Yu. A. 1967 The existence of supersonic zones in three-dimensional separated flows. J. Fluid Dyn. 2, 13–16. (Royal Aircraft Establishment Library Translation 1302, 1968.Google Scholar