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Direct Numerical Simulation of Swept-Wing Laminar Flow Control Using Pinpoint Suction

In: High Performance Computing in Science and Engineering '10

Author

Listed:
  • Tillmann A. Friederich

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

  • Markus J. Kloker

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

Abstract

Recent investigations of laminar flow control for swept-wing boundary-layer flows provide promising results with respect to crossflow-transition delay using a technique called pinpoint suction. Strong, localized suction through holes accurately positioned with respect to the crossflow-vortex position can directly weaken the growth of secondary instabilities that are responsible for the final laminar breakdown. With our incompressible code N3D extremely resolved grids in wall-normal direction have to be used to obtain numerical convergence. In order to confirm the results with such strong, localized suction, a single suction hole has been simulated in a Blasius boundary layer with the N3D code and additionally with our compressible code NS3D. Results from grid studies carried out for both codes as well as a comparison of the compressible/incompressible results are provided. Incompressible simulations with various pinpoint suction scenarios in the swept-wing flow show the application of successful pinpoint suction. Performance data for both codes focusing on a comparison of the NEC SX-8/SX-9 conclude this report.

Suggested Citation

  • Tillmann A. Friederich & Markus J. Kloker, 2011. "Direct Numerical Simulation of Swept-Wing Laminar Flow Control Using Pinpoint Suction," Springer Books, in: Wolfgang E. Nagel & Dietmar B. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering '10, pages 231-250, Springer.
    • Handle: RePEc:spr:sprchp:978-3-642-15748-6_18
    DOI: 10.1007/978-3-642-15748-6_18
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