Sound generation by shock–vortex interactions

Ito, Osamu; Hattori, Yuji

doi:10.1017/s0022112098003565

Cited by 172 publications

(187 citation statements)

References 25 publications

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“…It has been extensively studied experimentally (e.g. Dosanjh and Weeks [1965], Cattafesta and Settles [1992], Chang et al [2004]), analytically (Ribner [1954a(Ribner [ , 1985, Mahesh et al [1997]) and numerically (Ellzey et al [1995], Inoue and Hattori [1999], Dexun and Yanwen [2001]), with a particular emphasis on the noise production through the interaction. The passage of large coherent vortices through compression wave contributes significantly to the shock-associated noise that is found in jet engines.…”

Section: Shock / Vortex Interactionmentioning

confidence: 99%

“…The numerical set-up used here is similar to that of Inoue and Hattori Inoue and Hattori [1999]. A standing normal shock, corresponding to a free-stream Mach number M s is initialized at a location x -0.…”

Section: Shock / Vortex Interactionmentioning

confidence: 99%

“…The mean flow Mach number is M s = 1.29, and the vortex Mach number is M v = 0.39. Following the study of Inoue and Hattori Inoue and Hattori [1999], the Reynolds number based on the un-shocked density, velocity and viscosity, and on the vortex radius is set to Re = 800. Figure 3.26(a) represents the density field at a time T = 10.3R/a u .…”

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

“…Their behavior is typical of the quadrupolar nature of the phenomenon. The angular variations of the normalized pressure difference (P2 -Pp)/P s ) is then computed and compared to experimental and other numerical (Ellzey et al [1995], Inoue and Hattori [1999])…”

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

“…The shock-capturing scheme is used in the main flow direction within the shock thickness which extends over two cells, and up to three cells during the interaction. The shock-capturing scheme is also activated Dosanjh and Weeks [1965] and other numerical methods (Ellzey et al [1995], Inoue and Hattori [1999]). …”

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

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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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Section: Shock / Vortex Interactionmentioning

confidence: 99%

Section: Shock / Vortex Interactionmentioning

confidence: 99%

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

Section: P(r) = Pjl-^-±my-and T(r)=t U (L-^-±my-£mentioning

confidence: 99%

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Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Menon¹,

Génin²

2009

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Analysis of super compact finite difference method and application to simulation of vortex–shock interaction

2001

Numerical Methods in Fluids

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SUMMARYTurbulence and aeroacoustic noise high-order accurate schemes are required, and preferred, for solving complex flow fields with multi-scale structures. In this paper a super compact finite difference method (SCFDM) is presented, the accuracy is analysed and the method is compared with a sixth-order traditional and compact finite difference approximation. The comparison shows that the sixth-order accurate super compact method has higher resolving efficiency. The sixth-order super compact method, with a three-stage Runge-Kutta method for approximation of the compressible Navier -Stokes equations, is used to solve the complex flow structures induced by vortex -shock interactions. The basic nature of the near-field sound generated by interaction is studied.

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Robustness of the hybrid DRP‐WENO scheme for shock flow computations

Wan

Zhou

Sun

2011

Numerical Methods in Fluids

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SUMMARY This paper describes a new variant of hybrid scheme that is constructed by a wave‐capturing scheme and a nonoscillatory scheme for flow computations in the presence of shocks. The improved fifth‐order upwind weighted essentially nonoscillatory scheme is chosen to be conjugated with the seven‐point dispersion‐relation‐preserving scheme by means of an adaptive switch function of grid‐point type. The new hybrid scheme can achieve a better resolution than the hybrid scheme which is based on the classical weighted essentially scheme. Ami Harten's multiresolution analysis algorithm is applied to density field for detecting discontinuities and setting point values of the switch function adaptively. Moreover, the tenth‐order central filter is applied in smooth part of the flow field for damping dispersion errors. This scheme can promote overall computational efficiency and yield oscillation‐free results in shock flows. The resolution properties and robustness of the new hybrid scheme are tested in both 1D and 2D linear and nonlinear cases. It performs well for computing flow problems with rich structures of weak/strong shocks and large/small vortices, such as the shock‐boundary layer interaction problem in a shock tube, which illustrates that it is very robust and accurate for direct numerical simulation of gas‐dynamics flows. Copyright © 2011 John Wiley & Sons, Ltd.

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Sound generation by shock–vortex interactions

Cited by 172 publications

References 25 publications

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Analysis of super compact finite difference method and application to simulation of vortex–shock interaction

Robustness of the hybrid DRP‐WENO scheme for shock flow computations

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