Shock wave numerical structure and the carbuncle phenomenon

Chauvat, Yann; Moschetta, Jean‐Marc; Gressier, Jérémie

doi:10.1002/fld.916

Cited by 108 publications

(49 citation statements)

References 8 publications

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“…When applied to multi-dimensional flows, such one-dimensional approximations give rise to undesired numerical problems, especially for triangular or tetrahedral unstructured meshes [5]. For hypersonic applications, the carbuncle phenomenon takes place near the blunt nose region [6] and accurate computation of viscous flows with tetrahedral meshes remains a challenge [7]. Remedies for these numerical issues have been proposed and investigated but in general, lack robustness.…”

Section: Introductionmentioning

confidence: 99%

Numerical Computations of Hypersonic Boundary-Layer over Surface Irregularities

Chang

Choudhari

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Surface irregularities such as protuberances inside a hypersonic boundary layer may lead to premature transition on the vehicle surface. Early transition in turn causes large localized surface heating that could damage the thermal protection system. Experimental measurements as well as numerical computations aimed at building a knowledge base for transition Reynolds numbers with respect to different protuberance sizes and locations have been actively pursued in recent years. This paper computationally investigates the unsteady wake development behind large isolated cylindrical roughness elements and the scaled wind-tunnel model of the trip used in a recent flight measurement during the reentry of space shuttle Discovery. An unstructured mesh, compressible flow solver based on the space-time conservation element, solution element (CESE) method is used to perform time-accurate Navier-Stokes calculations for the flow past a roughness element under several wind-tunnel conditions. For a cylindrical roughness element with a height to the boundary-layer thickness ratio from 0.8 to 2.5, the wake flow is characterized by a mushroom-shaped centerline streak and horse-shoe vortices. While time-accurate solutions converged to a steady-state for a ratio of 0.8, strong flow unsteadiness is present for a ratio of 1.3 and 2.5. Instability waves marked by distinct disturbance frequencies were found in the latter two cases. Both the centerline streak and the horse-shoe vortices become unstable downstream. The oscillatory vortices eventually reach an early breakdown stage for the largest roughness element. Spectral analyses in conjunction with the computed root mean square variations suggest that the source of the unsteadiness and instability waves in the wake region may be traced back to possible absolute instability in the front-side separation region.

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Section: Introductionmentioning

confidence: 99%

Numerical Computations of Hypersonic Boundary-Layer over Surface Irregularities

Chang

Choudhari

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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show abstract

“…Remedies exist but in general, lack robustness. For hypersonic applications, carbuncle phenomenon takes place near the blunt nose region [2] and accurate computation of viscous flows with tetrahedral meshes remains a challenge [3].…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Viscous Flow Over Large Roughness Elements

Chang

Choudhari

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Viscous flow over discrete or distributed surface roughness has great implications for hypersonic flight due to aerothermodynamic considerations related to laminar-turbulent transition. Current prediction capability is greatly hampered by the limited knowledge base for such flows. To help fill that gap, numerical computations are used to investigate the intricate flow physics involved.An unstructured mesh, compressible Navier-Stokes code based on the space-time conservation element, solution element (CESE) method is used to perform time-accurate Navier-Stokes calculations for two roughness shapes investigated in wind tunnel experiments at NASA Langley Research Center. It was found through 2D parametric study that at subcritical Reynolds numbers of the boundary layers, absolute instability resulting in vortex shedding downstream, is likely to weaken at supersonic free-stream conditions. On the other hand, convective instability may be the dominant mechanism for supersonic boundary layers. Three-dimensional calculations for a rectangular or cylindrical roughness element at post-shock Mach numbers of 4.1 and 6.5 also confirm that no self-sustained vortex generation is present.

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“…Проблемы подобного плана обычно преодолеваются введением энтропийной коррекции [7] (ее введения оказывается недостаточно в случае достаточно силь-ных волн разрежения). Другие проблемы, возникающие при моделировании сверхзвукового обтекания затупленного тела, связаны с появлением грибовидного распределения плотности в окрестности точки торможения за фронтом головной ударной волны (carbuncle phenomenon) [8][9][10]. Методы, основанные на расщеплении вектора потока, не имеют указанной особенности.…”

Section: Introductionunclassified

WENO schemes for solution of unsteady one-dimensional gas dynamics test problems

Bulat¹,

Volkov²

2016

Naučno-teh. vestn. inf. tehnol. meh. opt.

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Shock wave numerical structure and the carbuncle phenomenon

Cited by 108 publications

References 8 publications

Numerical Computations of Hypersonic Boundary-Layer over Surface Irregularities

Numerical Computations of Hypersonic Boundary-Layer over Surface Irregularities

Hypersonic Viscous Flow Over Large Roughness Elements

WENO schemes for solution of unsteady one-dimensional gas dynamics test problems

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