Physical insight into a Mach 7.2 compression corner flow

Ritos, Konstantinos; Kokkinakis, Ioannis; Drikakis, Dimitris

doi:10.2514/6.2018-1810

Cited by 4 publications

(3 citation statements)

References 24 publications

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“…The present mesh spacing (∆y) is scaled using the conventional inner variable method ∆y + = u τ ∆y/ν w , where u τ = τ w /ρ w is the friction velocity, ν w is the near wall kinematic viscosity, τ w is the near wall shear stress, and ρ w is the near wall density. A mesh convergence study was performed in [21] with the two finer meshes, G2 and G3, showing close agreement in all calculated quantities and justifying the use of G3 in the further analysis.…”

Section: Hypersonic Flow Over a Compression/expansion Rampmentioning

confidence: 52%

“…This will allow to showcase similarities and differences between the various hypersonic boundary layers in the context of acoustic loading. The flow results for the STBLI case have been previously compared with available Direct Numerical Simulations (DNS) and experimental data [21], while the results for the transitional boundary layer presented here are based on a previous more detailed study by the authors [20].…”

Section: Introductionmentioning

confidence: 99%

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Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

et al. 2020

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This paper concerns a study of pressure fluctuations beneath hypersonic shockwave 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.

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Section: Hypersonic Flow Over a Compression/expansion Rampmentioning

confidence: 52%

Section: Introductionmentioning

confidence: 99%

Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

et al. 2020

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“…CNS3D can be used for implicit Large Eddy Simulations (iLES) and Direct Numerical Simulations (DNS) 12,[28][29][30] . There is also a Reynolds-Averaged Navier-Stokes (RANS) version of the code.…”

Section: Iles Frameworkmentioning

confidence: 99%

Insight Into Supersonic Combustion Using High-order Simulations

Kokkinakis

Drikakis

et al. 2022

Preprint

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High-order simulations of supersonic combustion are presented to advance understanding of the complex chemically-reacting flow processes and identify unknown mechanisms of the high-speed combustion process. We have employed 11th-order accurate implicit large-eddy simulations in conjunction with thermochemistry models comprising 20 chemical reactions. We compare the computations with available experiments and discuss the accuracy and uncertainties in both. Jets emanating from above and below the hydrogen plumes influence the combustion process and accuracy of the predictions. The simulations reveal that high temperatures are sustained for a long-distance downstream of the combustion onset. A barycentric map for the Reynolds stresses is employed to analyse the turbulent anisotropy. We correlate the axisymmetric contraction and expansion of turbulence with the interaction of reflected-shock waves with the supersonic combustion hydroxyl production regions. The physics insights presented in this study could potentially lead to more efficient supersonic combustion and scramjet technologies.

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Aeroacoustic Loading of Impinging Supersonic Boundary-Layer Interaction on Statically Deformed Surfaces

Kokkinakis,

Drikakis,

Michael Spottswood

et al. 2024

AIAA Journal

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This paper concerns the interaction of an impinging shock wave with a supersonic turbulent boundary layer over several distinct and permanently deformed surfaces, resulting in differences in the shock–boundary-layer interaction and the surface acoustic loading. High-order numerical simulations featuring two-dimensional surface deformations typically encountered in experiments are performed. The deformation amplitudes are up to half the incoming turbulent boundary-layer thickness. The results show that the high-pressure region about the shock impingement is significantly altered and can become narrower or wider depending on the local surface inclination of the deformed panel mode. The surface curvature is found to not significantly affect the separation and reattachment locations of the recirculation bubble. The power spectrum analysis of the pressure fluctuations along the panel’s midspan, where the surface attains the largest deformation amplitude, exhibits a rich and varied response. The pressure power spectrum is amplified in all of the surface deformation modes examined, with the magnitude of the amplification varying in the frequency domain, depending on the location and mode.

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Physical insight into a Mach 7.2 compression corner flow

Cited by 4 publications

References 24 publications

Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

Computational aeroacoustics beneath high speed transitional and turbulent boundary layers

Insight Into Supersonic Combustion Using High-order Simulations

Aeroacoustic Loading of Impinging Supersonic Boundary-Layer Interaction on Statically Deformed Surfaces

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