Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

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Abstract

This paper concerns a study of pressure fluctuations beneath hypersonic shock- wave turbulent boundary layer interactions and the associated acoustic loading on a compression/expansion ramp. We have employed high-order implicit large eddy simulations and conducted simulations at Mach 7.2. The spectral analysis of the pressure fluctuations at various locations of the compression/expansion ramp are compared with the spectra calculated beneath a hypersonic transitional boundary layer. Similarities and differences between the two hypersonic boundary layers, in the context of acoustic loading, are drawn. Extremely high values of pressure fluctuations are recorded after the shock re-attachement where the maximum pressure gradients are also observed, indicating that acoustic loading is correlated with areas of high pressure gradients. Finally, we show the impact of the boundary layer state (attached flow, turbulence bursts, recirculations, shock oscillations, shock re-attachment and expansion fans) on the frequency spectrum of the pressure fluctuations.
Original languageEnglish
PagesICCFD10-146
Number of pages15
Publication statusPublished - 14 Jul 2018
Event10th International Conference on Computational Fluid Dynamics - Barcelona, Spain
Duration: 9 Jul 201813 Jul 2018
http://www.iccfd.org/iccfd10/index.html

Conference

Conference10th International Conference on Computational Fluid Dynamics
Abbreviated titleICCFD10
CountrySpain
CityBarcelona
Period9/07/1813/07/18
Internet address

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Keywords

  • hypersonic flows
  • aeroacoustics
  • aerospace
  • transition
  • compressible flow
  • iLES

Cite this

Ritos, K., Drikakis, D., & Kokkinakis, I. W. (2018). Computational aeroacoustics beneath high speed transitional and turbulent boundary layers. ICCFD10-146. Paper presented at 10th International Conference on Computational Fluid Dynamics, Barcelona, Spain.