On the development of large-scale structures of a jet normal to a cross flow

Lim, Teng Joon; New, T. H.; Luo, S. C.

doi:10.1063/1.1347960

Cited by 154 publications

(94 citation statements)

References 38 publications

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“…Smith and Mungal [6] were able to corroborate this relationship in the near field of the jet for blowing ratios between 10 and 25. By scaling the data with the blowing ratio, Kamotani and Greber were able to account for different regimes associated with the blowing ratio (also equal to the square root of the momentum flux ratio).…”

Section: The Single Jicf: Unconfined Casesupporting

confidence: 61%

“…Kelso, Lim, and Perry [5] studied various flow features of the JICF for a range of velocity ratios from 2-6 using hot-wire anemometry to examine the evolution of shear layer roll-up. Lim, New and Luo [6] then conducted a qualitative experiment on vortex formation by releasing a dye tracer at specific locations around the issuing jet. They found that the shear layer vortices that develop at the jet/crossflow interface coalesce as the jet propagates and eventually create the counterrotating vortex pair.…”

Section: Introductionmentioning

confidence: 99%

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Confined Mixing of Multiple Transverse Jets

Bishop¹

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. Results for two jets indicate monotonically decreasing unmixednessfor the range of conditions tested, with no local optimum apparent. Data for three jets indicate a local optimum at ( ⁄ ) and relatively flat range of mixing performance in the range of ( ⁄ ). Six jets indicate a minimum unmixedness near ( ⁄ ) , but exhibited poorer mixing performance than all other configurations at the highest values of ( ⁄ ) tested. The most optimum configuration tested was six jets at ( ⁄ ) , resulting in an unmixedness of 0.0192. This value was 76% lower than the next lowest configuration (three jets) at the same ( ⁄ ) Total momentum was found to collapse the data well, as configurations more closely matched a historical correlation for second moment of a single confined jet more closely.

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Section: The Single Jicf: Unconfined Casesupporting

confidence: 61%

Section: Introductionmentioning

confidence: 99%

Confined Mixing of Multiple Transverse Jets

Bishop¹

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“…Similar large scale structures are known to exist even in low-speed JICF due to KelvinHelmholtz instabilities (KHI) (Fric and Roshko [2004]) of the vortex sheet created at the jet nozzle. These KHI occur along the windward and the lateral sides of the jet, forming a circumferential vortical structure rather than a vortex ring, as originally thought (Lim et al [2001]). …”

Section: Unsteady Features and Flow Dynamicsmentioning

confidence: 97%

“…Andreopoulos [1985], Yuan et al [1999], Lim et al [2001], New et al [2003]). Past experimental studies of JICF in supersonic crossflows have suggested that some of these vortical structures were also observed in supersonic JICF (VanLerberghe et al [2000], BenYakar et al [2006]).…”

Section: Chapter V Sonic Jet In Supersonic Cross-flowmentioning

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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“…The behaviour of these vortices depends on jet-to-crossflow velocity ratio, R = U j /U ∞ ; jet pressure, p j ; jet Reynolds number, Re dj = U j d j /ν j ; and jet pipe geometry [17]. Several authors [11,[18][19][20] have proposed different mechanisms for the development and evolution of jet shear-layer vortices in a subsonic crossflow. Smith and Mungal [21] observed that the formation of the jet shear-layer vortices is delayed in a subsonic crossflow with increased velocity ratios R > 5.…”

Section: Introductionmentioning

confidence: 99%

Transient interaction between a reaction control jet and a hypersonic crossflow

et al. 2018

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This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream, and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet, and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate. * warrick.miller@adelaide.edu.au.

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On the development of large-scale structures of a jet normal to a cross flow

Cited by 154 publications

References 38 publications

Confined Mixing of Multiple Transverse Jets

Confined Mixing of Multiple Transverse Jets

Hybrid LES of Detonations in Reacting Multi-Phase Mixtures

Transient interaction between a reaction control jet and a hypersonic crossflow

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