A nonlinear compressible flow disturbance formulation for adaptive mesh refinement wavepacket tracking in hypersonic boundary-layer flows

Browne, Oliver M.; Haas, Anthony P.; Fasel, Hermann F.; Brehm, Christoph

doi:10.1016/j.compfluid.2022.105395

Cited by 19 publications

(9 citation statements)

References 21 publications

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“…To examine if the nonlinear nature of the governing equations affects the mode coupling, we computed the disturbance flow field by solving the nonlinear disturbance equations (Browne et al. 2022), which does not neglect the nonlinear terms in the disturbance flow equation. The disturbance amplitude was chosen small enough such that the maximum pressure amplitude observed in the entire computational domain did not exceed 1 % of the free-stream pressure value.…”

Section: Resultsmentioning

confidence: 99%

On the role of discrete and continuous modes in a cooled high-speed boundary layer flow

2022

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The disturbance flow field for a Mach $6$ flat-plate boundary layer flow with a wall-to-free-stream temperature ratio of $0.5$ is studied using direct numerical simulation (DNS), linear stability theory (LST) and biorthogonal decomposition. In the second-mode instability region, the DNS flow field can be reconstructed using a single LST mode, namely $F^+_1$ . However, when the supersonic mode emerges, none of the discrete modes nor the continuous branches alone can precisely match the DNS data. A superposition of the pair of discrete supersonic modes $F^\pm _1$ and the slow acoustic continuous spectrum is required to reproduce the disturbance amplitude distributions and the amplification rates observed in the DNS. Another finding is that the supersonic mode $F^-_1$ , which should be decaying following LST, in actuality is amplified based on the projected DNS data.

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Section: Resultsmentioning

confidence: 99%

On the role of discrete and continuous modes in a cooled high-speed boundary layer flow

2022

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“…The AMR disturbance flow tracking (AMR-DFT) method is employed to simulate particle interactions with high-speed boundary layers. For more details about the AMR-DFT approach, also previously referred to as AMR wavepacket tracking (AMR-WPT), the reader is referred to Browne et al (2017Browne et al ( , 2019aBrowne et al ( , 2022Browne et al ( , 2020a. Briefly, the AMR-DFT approach employs an overset dual mesh approach, comprised of a baseflow mesh and a disturbance flow mesh.…”

Section: The Amr Disturbance Flow Tracking Simulation Approachmentioning

confidence: 99%

“…The AMR tracks the particle along its trajectory before impingement to capture important flow features and then tracks the generated wavepacket inside the boundary layer after the particle impingement. Several recent works (see Browne et al 2017Browne et al , 2019aBrowne et al , 2022Browne et al , 2020a demonstrated that AMR can be employed for tracking the first-and second-mode dominated wavepackets in high-speed boundary layers with high computational efficiency. A blended fifth-order accurate weighted essentially non-oscillatory scheme (Brehm et al 2015;Brehm 2017) was employed for spatial discretization of the convective terms, and a standard second-order centred finite difference scheme was used for the viscous terms.…”

Section: The Amr Disturbance Flow Tracking Simulation Approachmentioning

confidence: 99%

“…For more details about the AMR-DFT approach, also previously referred to as AMR wavepacket tracking (AMR-WPT), the reader is referred to Browne et al. (2017, 2019 a , 2022, 2020 a ). Briefly, the AMR-DFT approach employs an overset dual mesh approach, comprised of a baseflow mesh and a disturbance flow mesh.…”

Section: Governing Equations and Numerical Simulation Approachmentioning

confidence: 99%

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Biorthogonal decomposition of the disturbance flow field generated by particle impingement on a hypersonic boundary layer

A. Al Hasnine,

Russo,

Tumin

et al. 2023

J. Fluid Mech.

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The disturbance flow field in a hypersonic boundary layer excited by particle impingement was investigated with a focus on the first stage of the laminar-to-turbulent transition process, namely the receptivity process. A previously validated direct numerical simulation approach adopting disturbance flow tracking is used to simulate the particle-induced transition process. Particle impingement generates a highly complex disturbance flow field that can be characterised by a wide range of frequencies and wavenumbers. After providing some insight about the spectral characteristics of the disturbance flow field in the frequency and wavenumber domains, biorthogonal decomposition is employed to reveal the composition of the disturbance flow field consisting of different continuous and discrete eigenmodes that are triggered through particle impingement. The disturbance flow characteristics for different frequency and wavenumber pairs are discussed where large contributions in the disturbance flow spectrum are observed in the vicinity of the impingement location. A significant amount of the disturbance energy is diverted into the free stream leading to large coefficients of projection for the slow and fast acoustic branches while contributions to the entropy and vorticity branches are negligible. In addition to the continuous acoustic spectra, the first-, second- and other higher-order Mack modes are activated and provide large contributions to the disturbance flow field inside the boundary layer. Finally, it is demonstrated that the disturbance flow field in the vicinity of the impingement location can be reconstructed with a maximum relative error of $2.3\,\%$ by employing a theoretical biorthogonal eigenfunction system expansion and by considering contributions from fast and slow acoustic waves and at most four discrete modes only.

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“…For larger initial disturbance amplitudes (i.e., q ∼ q) and/or when the disturbances reach the nonlinear transition regime, the nonlinear disturbance terms in the governing equations become significant and need to be evaluated to accurately capture the mechanisms driving transition. A more detailed discussion of the derivation and some of the intricacies of the disturbance flow equations and its numerical solution procedure are given in [35,50,51].…”

Section: Adaptive Mesh Refinement Wave Packet Tracking (Amr-wpt)mentioning

confidence: 99%

Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6

Araya

Bitter

Wheaton

et al. 2022

AIAA AVIATION 2022 Forum

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Boundary-layer instabilities for a finned cone at Mach = 6, Re = 8.4 × 10 6 [ −1 ], and zero incidence angle are examined using linear stability methods of varying fidelity and maturity, following earlier analysis presented in [1]. The geometry and laminar flow conditions correspond to experiments conducted at the Boeing Air Force Mach 6 Quiet Tunnel (BAM6QT) at Purdue University. Where possible, a common mean flow is utilized among the stability computations, and comparisons are made along the acreage of the cone where transition is first observed in the experiment. Stability results utilizing Linear Stability Theory (LST), planar Parabolized Stability Equations (planar-PSE), One-Way Navier Stokes (OWNS), forced direct numerical simulation (DNS), and Adaptive Mesh Refinement Wavepacket Tracking (AMR-WPT) are presented. A dominant three-dimensional vortex instability occurring at ≈ 250 kHz is identified that correlates well with experimental measurements of transition onset. With the exception of LST, all of the higher-fidelity linear methods considered in this work were consistent in predicting the initial growth and general structure of the vortex instability as it evolved downstream. Some of the challenges, opportunities, and development needs of the stability methods considered are discussed.

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A nonlinear compressible flow disturbance formulation for adaptive mesh refinement wavepacket tracking in hypersonic boundary-layer flows

Cited by 19 publications

References 21 publications

On the role of discrete and continuous modes in a cooled high-speed boundary layer flow

On the role of discrete and continuous modes in a cooled high-speed boundary layer flow

Biorthogonal decomposition of the disturbance flow field generated by particle impingement on a hypersonic boundary layer

Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6

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