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)


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].


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.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. 1.
    Berland, J., Bogey, C., Bailly, C.: Numerical study of screech generation in a planar supersonic jet. Physics of fluids 19 (2007), doi:10.1063/1.2747225Google Scholar
  2. 2.
    Desquesnes, G., et al.: On the use of a high order overlapping grid method for coupling in CFD/CAA. J. Comp. Phys. 220, 355–382 (2006)zbMATHCrossRefMathSciNetGoogle Scholar
  3. 3.
    Guenanff, R., Sagaut, P., Manoha, E., Terracol, M., Lewandowski, R.: Theoretical aspects of a multi-domain high-order method for CAA. AIAA Paper 2003-3117 (2003)Google Scholar
  4. 4.
    Lele, S.: Compact finite difference schemes with spectral-like resolution. J. Comp. Phys. 103, 16–42 (1992)zbMATHCrossRefMathSciNetGoogle Scholar
  5. 5.
    Marsden, O., Bogey, C., Bailly, C.: High-Order Curvilinear Simulations of Flows Around Non-Cartesian Bodies. J. Comp. Aeroacoustics 13(4), 731–748 (2004)CrossRefGoogle Scholar
  6. 6.
    Powell, A.: On the mechanism of choked jet noise. Proc. Phys. Soc. London B66, 1039–1056 (1953)Google Scholar
  7. 7.
    Schulze, J., Schmid, P., Sesterhenn, J.: Exponential time integration using Krylov subspaces. Int. J. Numer. Meth. Fluids (2008), doi:10.1002/fld.1902Google Scholar
  8. 8.
    Schulze, J., et al.: Numerical Simulation of Supersonic Jet Noise. Num. Sim. Turbulent Flows & Noise Generation, NNFM 104, 29–46 (2009)CrossRefGoogle Scholar
  9. 9.
    Sesterhenn, J.: A characteristic-type formulation of the Navier-Stokes equations for high order upwind schemes. Computers & Fluids 30(1), 37–67 (2001)zbMATHCrossRefGoogle Scholar
  10. 10.
    Sherer, S., Scott, J.: High order compact finite-difference methods on general overset grids. J. Comp. Phys. 210, 459–496 (2005)zbMATHCrossRefGoogle Scholar
  11. 11.
    Tam, C., Ahuja, K., Jones III, R.: Screech Tones from Free and Ducted Supersonic Jets. AIAA J. 32 (5), 917–922 (1994)CrossRefGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2010

Authors and Affiliations

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

Personalised recommendations