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Numerical Simulation of Supersonic Jet Noise with Overset Grid Techniques

  • J. Schulze
  • J. Sesterhenn
Conference paper
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 110)

Abstract

Supersonic jets with a complex shock pattern appear in numerous technical applications. Most supersonic jets, especially in modern military or civil aircraft, are not perfectly expanded. Thereby, shocks are appearing in the jet core and interacting with the turbulent mixing-layers and emanating shock induced noise. Under certain conditions this upstream traveling noise can be amplified due to a closed feedback loop. These so called screech tones can reach sound pressure levels of up to 160 dB [11] and hence lead to immense noise pollution and even structural fatigue.

The focus of this research project lies in the numerical simulation of supersonic jet noise and finally the minimization of screech tones with an adjoint shape optimization approach of the nozzle geometry. To this end the nozzle geometry, based on a complex shape, has to be included in the computational domain. In the present paper the method of overset grid techniques is presented for the simulation of supersonic jet noise. Direct numerical simulations with a modeled nozzle inlet showed a good agreement of the screech frequency to a semi-empirical low found by Powell in 1953 [6].

Keywords

Direct Numerical Simulation Message Passing Interface Cartesian Grid Nozzle Geometry Curvilinear Grid 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2010

Authors and Affiliations

  • J. Schulze
    • 1
  • J. Sesterhenn
    • 1
  1. 1.Institut für Mathematik und RechneranwendungNeubibergGermany

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