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Direct Numerical Simulation of a Serrated Nozzle End for Jet-Noise Reduction

In: High Performance Computing in Science and Engineering `07

Author

Listed:
  • A. Babucke

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

  • M. Kloker

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

  • U. Rist

    (Universität Stuttgart, Institut für Aerodynamik und Gasdynamik)

Abstract

Sound generation of a subsonic laminar jet has been investigated using direct numerical simulation (DNS). The simulation includes the nozzle end, modelled by a finite flat splitter plate with Mach numbers of MaI = 0.8 above and MaII = 0.2 below the plate. Behind the nozzle end, a combination of wake and mixing layer develops. Due to its instability, roll up and pairing of spanwise vortices occur, with the vortex pairing being the major acoustic source. As a first approach for noise reduction, a rectangular notch at the trailing edge is investigated. It generates longitudinal vortices and a spanwise deformation of the flow downstream of the nozzle end. This leads to a an early breakdown of the large spanwise vortices and accumulations of small-scale structures. Compared to a two-dimensional simulation performed earlier [3], the emitted sound is reduced by 6 dB.

Suggested Citation

  • A. Babucke & M. Kloker & U. Rist, 2008. "Direct Numerical Simulation of a Serrated Nozzle End for Jet-Noise Reduction," Springer Books, in: Wolfgang E. Nagel & Dietmar Kröner & Michael Resch (ed.), High Performance Computing in Science and Engineering `07, pages 319-337, Springer.
    • Handle: RePEc:spr:sprchp:978-3-540-74739-0_22
    DOI: 10.1007/978-3-540-74739-0_22
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