TY - CONF
T1 - Computational aeroacoustics beneath high speed transitional and turbulent boundary layers
AU - Ritos, K.
AU - Drikakis, D.
AU - Kokkinakis, I. W.
N1 - Funding Information:
This work was sponsored by the Air Force Office of Scientific Research, Air Force Material Command, USAF, under grant number FA9550-14-1-0224. The U.S. Government is authorised to reproduce and distribute reprints for Governmental purpose notwithstanding any copyright notation thereon. The authors would like to thank S. M. Spottswood, Z. Riley and D. Garner for their support. The authors would also like to thank EPSRC for providing access to computational resources on the National HPC facility ARCHER (http://www.archer.ac.uk) through the UK Applied Aerodynamics Consortium Leadership Project “e529”.
Publisher Copyright:
© ICCFD 2018.
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2018
Y1 - 2018
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 - Aeroacoustics
KW - Compressible flow
KW - Hypersonic flows
KW - ILES
KW - Transition
UR - http://www.scopus.com/inward/record.url?scp=85090857246&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:85090857246
T2 - 10th International Conference on Computational Fluid Dynamics, ICCFD 2018
Y2 - 9 July 2018 through 13 July 2018
ER -