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Direct Numerical Simulation of Film Cooling in Hypersonic Boundary-Layer Flow

In: High Performance Computing in Science and Engineering '08

Author

Listed:
  • J. Linn

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

  • M. J. Kloker

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

Abstract

Summary Effusion cooling by discrete slits and holes in various laminar zero-pressure gradient super- and hypersonic boundary layers is investigated using direct numerical simulation. For an adiabatic Mach-6 boundary layer it was found that slits are better than holes due to the lower blowing velocity. Slit blowing causes a destabilisation of 2 nd -mode disturbances, and a complete stabilisation of 1 st modes despite the generated maxima of the spanwise vorticity inside the boundary layer. Hole blowing gives rise to counter-rotating streamwise vortices, with a noticeable laminar-flow destabilisation only for large spanwise hole spacings. Computational aspects such as the performance of the numerical code on the supercomputer NEC SX-8 and optimization of the code are also discussed.

Suggested Citation

  • J. Linn & M. J. Kloker, 2009. "Direct Numerical Simulation of Film Cooling in Hypersonic Boundary-Layer Flow," Springer Books, in: Wolfgang E. Nagel & Dietmar B. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering '08, pages 171-189, Springer.
    • Handle: RePEc:spr:sprchp:978-3-540-88303-6_13
    DOI: 10.1007/978-3-540-88303-6_13
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