Hypersonic flow over spherically blunted double cones

Hao, Jiaao; Wen, Chih-Yung

doi:10.1017/jfm.2020.331

Cited by 26 publications

(11 citation statements)

References 48 publications

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“…The numerical simulations in this study are performed using an in-house multi-block parallel finite-volume solver called PHAROS (Hao, Wang & Lee 2016; Hao & Wen 2020). The modified Steger–Warming scheme (MacCormack 2014) extended to a higher order by the monotone upstream-centred schemes for conservation law reconstruction (van Leer 1979) is used to calculate the inviscid fluxes, whereas a second-order central difference is used to compute the viscous fluxes.…”

Section: Computational Detailsmentioning

confidence: 99%

Occurrence of global instability in hypersonic compression corner flow

2021

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Section: Computational Detailsmentioning

confidence: 99%

Occurrence of global instability in hypersonic compression corner flow

2021

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“…The base-flow solutions are obtained using an in-house multiblock parallel finite-volume solver called PHAROS (Hao, Wang & Lee 2016; Hao & Wen 2020). The inviscid fluxes are calculated using the modified Steger–Warming scheme (MacCormack 2014), while the viscous fluxes are computed with the second-order central difference.…”

Section: Computational Detailsmentioning

confidence: 99%

Response of hypersonic compression corner flow to upstream disturbances

2023

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Hypersonic flow over a two-dimensional compression corner is investigated using computational fluid dynamics and global resolvent analysis in this study, which is a continuation of the work done by Hao et al. (J. Fluid Mech., vol. 919, 2021, p. A4). The same baseline free-stream conditions with a Mach number of 7.7 and a unit Reynolds number of 4.2 × 106 m−1 are considered. The ramp angles range from 0° (equivalent to a flat plate) to 12° (slightly below the critical angle of global instability). During this process, the base flow evolves from no separation to incipient separation to large separation. The resolvent analysis reveals that the optimal response to upstream disturbances localised near the leading edge is in the form of steady streamwise streaks for all interaction strengths, which arise from transient growth in the flat-plate boundary layer due to the lift-up mechanism and significantly grow near the corner due to the Görtler instability. The most amplified spanwise wavelength decreases as the ramp angle is increased and scales with the incoming boundary-layer thickness.

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“…The 2-D and 3-D simulations are performed using an in-house finite-volume solver called PHAROS (Hao, Wang & Lee 2016; Hao & Wen 2020). The inviscid fluxes are calculated using the modified Steger–Warming scheme (MacCormack 2014), while the viscous fluxes are computed with a second-order central difference.…”

Section: Computational Detailsmentioning

confidence: 99%

On the low-frequency unsteadiness in shock wave–turbulent boundary layer interactions

Hao

2023

J. Fluid Mech.

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The shock wave–turbulent boundary layer interaction over a compression corner is studied using global stability analysis (GSA) and resolvent analysis based on a separation of scales between the low-frequency, large-scale motions and the turbulent fluctuations. The GSA identifies a leading stationary mode, which becomes globally unstable as the ramp angle is beyond a critical value. For globally stable flows, the resolvent analysis captures two-dimensional and three-dimensional local maxima in optimal gain, both of which are due to modal resonance between the forcing and the leading global mode. Notably, the frequency-premultiplied optimal gain associated with two-dimensional disturbances peaks at a low frequency. For different interaction strengths, the peak frequencies collapse onto a universal value of 0.015 when non-dimensionalized using the length of the separation region and the free-stream velocity. A numerical simulation perturbed with the corresponding optimal forcing reveals that the response is in the form of a back-and-forth shock motion.

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Hypersonic flow over spherically blunted double cones

Cited by 26 publications

References 48 publications

Occurrence of global instability in hypersonic compression corner flow

Occurrence of global instability in hypersonic compression corner flow

Response of hypersonic compression corner flow to upstream disturbances

On the low-frequency unsteadiness in shock wave–turbulent boundary layer interactions

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