The interaction of a shock with a vortex: Shock distortion and the production of acoustic waves

Ellzey, Janet L.; Henneke, Michael; Picone, J. M.; Oran, Elaine S.

doi:10.1063/1.868738

Cited by 111 publications

(86 citation statements)

References 14 publications

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“…54 The reflected shock waves from the upper 10 and lower walls of the ejector interact with the two vortex cores and their propagation is altered, an observation consistent with Ellzey et al 55 Focusing on the lower vortex core which is rotating clockwise, we notice that the portion of the reflected shock wave to the right of the core travels more slowly; at the same time the portion of the reflected shock to the left of the core, which has just been reflected from the underside of the nozzle is also slowed down. The shock wave splitting phenomenon produces secondary shock waves which add to the complexity of our already intricate flow.…”

Section: Diffraction Regionsupporting

confidence: 73%

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Zare‐Behtash

Kontis

2009

Journal of Propulsion and Power

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An experimental study has been conducted to examine the interaction of compressible flow structures such as shocks and vortices with a 2-D ejector geometry using a shock tube facility.Three diaphragm pressure ratios of P 4 /P 1 = 4, 8, and 12 have been employed, where P 4 is the driver gas pressure and P 1 is the pressure within the driven compartment of the shock tube. These lead to incident shock Mach numbers of M s = 1.34, 1.54, and 1.66, respectively. The length of the driver section of the shock tube was 700 mm. Air was used for both the driver and driven gases.

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Section: Diffraction Regionsupporting

confidence: 73%

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Zare‐Behtash

Kontis

2009

Journal of Propulsion and Power

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“…43 These authors simulated the test problem at very low Reynolds numbers using Direct Numerical Simulation (DNS). The effects of the Reynolds number on the physical phenomena taking place during the shock-vortex interaction were found to be very small, which is also supported by good comparisons 42 between results obtained from DNS and from the Euler simulations performed by Ellzey et al 51 for slightly different flow parameters. This led us to compute the shock-vortex problem from the 2-D Euler equations (3) …”

Section: Shock-vortex Interactionsupporting

confidence: 69%

Self-Adjusting Shock-Capturing Spatial Filtering for High-Order Non-Linear Computations

Bogey

Cacqueray

Bailly

2008

14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference)

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A shock-capturing methodology is developed for non-linear computations using lowdissipation schemes and centered finite differences. It consists in applying an adaptative second-order filtering to handle discontinuities in combination with a background selective filtering to remove grid-to-grid oscillations. The shock-capturing filtering is written in its conservative form, and its magnitude is determined dynamically from the flow solutions. A shock-detection procedure based on a Jameson-like shock sensor is derived. A secondorder filter with reduced errors in the Fourier space with respect to the standard secondorder filter is also designed. Linear and non-linear problems are solved to show that the methodology is capable of capturing shocks without providing dissipation outside shocks. The shock detection allows in particular to distinguish shocks from linear waves, and from vortices when it is performed from dilatation rather than from pressure.

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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%

“…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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The interaction of a shock with a vortex: Shock distortion and the production of acoustic waves

Cited by 111 publications

References 14 publications

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Compressible Flow Structures Interaction with a Two-Dimensional Ejector: A Cold-Flow Study

Self-Adjusting Shock-Capturing Spatial Filtering for High-Order Non-Linear Computations

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

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