Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

Research output: Contribution to conferencePaper

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.

Conference

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

Fingerprint

Computational aeroacoustics
Boundary layers
Acoustics
Hypersonic aerodynamics
Pressure gradient
Hypersonic boundary layers
Large eddy simulation
Shock waves
Spectrum analysis
Mach number
Fans
Compaction
Turbulence

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.
Ritos, K. ; Drikakis, D. ; Kokkinakis, I. W. / Computational aeroacoustics beneath high speed transitional and turbulent boundary layers. Paper presented at 10th International Conference on Computational Fluid Dynamics, Barcelona, Spain.15 p.
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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.",
keywords = "hypersonic flows, aeroacoustics, aerospace, transition, compressible flow, iLES",
author = "K. Ritos and D. Drikakis and Kokkinakis, {I. W.}",
note = "Paper number: ICCFD10-146.; 10th International Conference on Computational Fluid Dynamics, ICCFD10 ; Conference date: 09-07-2018 Through 13-07-2018",
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Ritos, K, Drikakis, D & Kokkinakis, IW 2018, 'Computational aeroacoustics beneath high speed transitional and turbulent boundary layers' Paper presented at 10th International Conference on Computational Fluid Dynamics, Barcelona, Spain, 9/07/18 - 13/07/18, pp. ICCFD10-146.

Computational aeroacoustics beneath high speed transitional and turbulent boundary layers. / Ritos, K.; Drikakis, D.; Kokkinakis, I. W.

2018. ICCFD10-146 Paper presented at 10th International Conference on Computational Fluid Dynamics, Barcelona, Spain.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

AU - Ritos, K.

AU - Drikakis, D.

AU - Kokkinakis, I. W.

N1 - Paper number: ICCFD10-146.

PY - 2018/7/14

Y1 - 2018/7/14

N2 - 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.

AB - 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.

KW - hypersonic flows

KW - aeroacoustics

KW - aerospace

KW - transition

KW - compressible flow

KW - iLES

M3 - Paper

SP - ICCFD10-146

ER -

Ritos K, Drikakis D, Kokkinakis IW. Computational aeroacoustics beneath high speed transitional and turbulent boundary layers. 2018. Paper presented at 10th International Conference on Computational Fluid Dynamics, Barcelona, Spain.