Conservative Hybrid Compact-WENO Schemes for Shock-Turbulence Interaction

Pirozzoli, Sergio

doi:10.1006/jcph.2002.7021

Cited by 414 publications

(339 citation statements)

References 49 publications

(101 reference statements)

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“…No doubt, WENO [8][9][10] and it's derived schemes are of the most successful ones. Especially, some low dissipative WENO type schemes have been proposed, such as compact-WENO [11,12], WENO-Z [13], WENO-SYMBO [14], TWENO [15], which have been successfully used for multi-scales capture. As Pirozzoli [16] reviewed and suggested that the hybridization of a high-order compact scheme with the WENO scheme is good choice for the DNS and larger eddy simulation (LES) of turbulent compressible flows.…”

Section: Introductionmentioning

confidence: 99%

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Liang

2014

Commun. Comput. Phys.

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Abstract. In this paper, direct numerical simulation (DNS) is presented for spatially evolving turbulent boundary layer over an isothermal flat-plate at Ma ∞ = 2.25,5,6,8. When Ma ∞ = 8, two cases with the ratio of wall-to-reference temperature T w /T ∞ = 1.9 and 10.03 are considered respectively. The wall temperature approaches recovery temperatures for other cases. The characteristics of compressible turbulent boundary layer (CTBL) affected by freestream Mach number and wall temperature are investigated. It focuses on assessing compressibility effects and the validity of Morkovin's hypothesis through computing and analyzing the mean velocity profile, turbulent intensity, the strong Reynolds analogy (SRA) and possibility density function of dilatation term. The results show that, when the wall temperature approaches recovery temperature, the effects of Mach number on compressibility is insignificant. As a result, the compressibility effect is very weak and the Morkovin's hypothesis is still valid for Mach number even up to 8. However, when Mach number equal to 8, the wall temperature effect on the compressibility is sensitive. In this case, when T w /T ∞ = 1.9, the Morkovin's hypothesis is not fully valid. The validity of classical SRA depends on wall temperature directly. A new modified SRA is proposed to eliminate such negative factor in near wall region. Finally the effects of Mach number and wall temperature on streaks are also studied.

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Section: Introductionmentioning

confidence: 99%

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Liang

2014

Commun. Comput. Phys.

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“…The state-of-the-art applications of high-order and high-accurate methods in complex grids are still limited, while there are many kinds of high-order schemes, such as compact schemes [5][6][7]33,35], WCNSs [9,10], ENO [37,38] and WENO schemes [2,3,39,52,53], DG schemes [40-44, 48, 49, 51, 54], spectral methods (including spectral element (SE) [55], SV [56,57,110], spectral difference (SD) [58], staggered spectral methods [60]), gas-kinetic schemes (GKS) [61,[63][64][65], dispersion-relation-preserving (DRP) schemes [67], low dissipative high-order schemes [68], monotonicity preserving (MP) schemes [69,70], group velocity control (GVC) schemes [71,72], SPH methods [45,62], ALE methods [64][65][66]81], methods for multiphase flows [42,46,47], and many hybrid ones [73][74][75][76]. In most published articles and reviews, the flows are complex with shock...…”

Section: High-order and High Accurate Cfd Methods For Complex Grid Prmentioning

confidence: 99%

“…In order to dealing with shock wave problems, Adams and Shariff [74] have developed a compact-ENO scheme. Pirozzoli [75] have developed a compact-WENO scheme which was further improved by Ren et al [73]. Deng et al have developed compact nonlinear schemes [8] and weighted compact nonlinear schemes (WCNS) [9,10].…”

Section: Introductionmentioning

confidence: 99%

High-Order and High Accurate CFD Methods and Their Applications for Complex Grid Problems

Deng

Mao

et al. 2012

Commun. comput. phys.

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Abstract. The purpose of this article is to summarize our recent progress in high-order and high accurate CFD methods for flow problems with complex grids as well as to discuss the engineering prospects in using these methods. Despite the rapid development of high-order algorithms in CFD, the applications of high-order and high accurate methods on complex configurations are still limited. One of the main reasons which hinder the widely applications of these methods is the complexity of grids. Many aspects which can be neglected for low-order schemes must be treated carefully for high-order ones when the configurations are complex. In order to implement highorder finite difference schemes on complex multi-block grids, the geometric conservation law and block-interface conditions are discussed. A conservative metric method is applied to calculate the grid derivatives, and a characteristic-based interface condition is employed to fulfil high-order multi-block computing. The fifth-order WCNS-E-5 proposed by Deng [9, 10] is applied to simulate flows with complex grids, including a double-delta wing, a transonic airplane configuration, and a hypersonic X-38 configuration. The results in this paper and the references show pleasant prospects in engineering-oriented applications of high-order schemes.

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“…However, compact schemes are poorly suited to the resolution of transonic to supersonic flows, creating high amplitude, unphysical oscillations, and much work has been devoted to the stabilization of these schemes in shock-containing flows, spanning from artificial diffusion (Cook and Cabot [2004], Kawai and Lele [2008]) to the application of adaptive filters, reducing the accuracy in close shock regions only (Visbal and Gaitonde [2005]). In the context of hybrid methods, these compact schemes have been combined to TVD (Rizzetta et al [2001]), ENO (Adams and Shariff [1996]) or WENO (Pirozzoli [2002], Ren et al [2003]) schemes and have been found well suited to simple canonical flows. However, extension to complex (practical) geometries and parallelization of such codes is difficult (Hill and Pullin [2004]), and the computational cost of these schemes is rather high, which makes such schemes unadapted to full scale simulations.…”

Section: Numerical Issues In Supersonic Turbulent Flows Computationsmentioning

confidence: 99%

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Menon¹,

Génin²

2009

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REPORT DOCUMENTATION PAGEThe public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid 0MB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) 28-02-2009 2. REPORT TYPE Final Report DATES COVERED {From -To)December 1 PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)School of Aerospace Engineering Georgia Institute of Technology Atlanta, GA 30332 PERFORMING ORGANIZATION REPORT NUMBERCCL-TR-2009-02-1 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)AFOSR/NL 4015 Wilson Blvd ? Arlington, VA 22203 Dr. Fariba Fahroo SPONSOR/MONITORS ACRONYM(S)AFOSR/NM SPONSOR/MONITORS REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTUnlimited, Unclassified SUPPLEMENTARY NOTES ABSTRACTA Large-Eddy Simulation (LES) methodology adapted to the resolution of high Reynolds number turbulent flows in supersonic conditions was proposed and developed. A novel numerical scheme was designed, that switches from a low-dissipation central scheme for turbulence resolution to a flux difference splitting scheme in regions of discontinuities. A state-of-the-art closure model was extended in order to take compressibility effects and the action of shock / turbulence interaction into account. The proposed method was validated and employed for the study of shock / turbulent shear layer interaction as a mixing-augmentation technique, and highlighted the efficiency in mixing improvement after the interaction, but also the limited spatial extent of this turbulent enhancement. A second study focused on the injection of a sonic jet normally to a supersonic crossflow. The validity of the simulation was assessed by comparison with experimental data, and the dynamics of the interaction was examined. The sources of vortical structures were identified, with a particular emphasis on the impact of the flow speed onto the vortical evolution. It is shown that the developed hybrid methodology permits a capture of shock / turbulence interactions in direct simulations that agrees well with other reference simulations, and that the LES methodology effectively reproduces the turbulence evolution and physical phenomena involved in the interaction. This numerical approach is then employed to study a problem of practical importance in high-speed mixing. The inter...

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Conservative Hybrid Compact-WENO Schemes for Shock-Turbulence Interaction

Cited by 414 publications

References 49 publications

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

High-Order and High Accurate CFD Methods and Their Applications for Complex Grid Problems

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

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