Sonic Injection from Diamond-Shaped Orifices into a Supersonic Crossflow

Tomioka, Sadatake; Jacobsen, Lance; Schetz, Joseph A.

doi:10.2514/2.6086

Cited by 72 publications

(27 citation statements)

References 14 publications

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“…It was concluded that, at lower jet-tofreestream dynamic pressure ratio, the fuel jet penetration was higher from a diamond-shaped orifice as compared to an equivalent circular injector. At high dynamic pressure ratios, the performance of diamond-shaped and equivalent circular injector were same [58]. Also, adding sweepback and a moderate yaw angle to the sweepback, greatly enhanced the penetration depth obtained using diamond-shaped injector, which is unlikely in the case of a circular injector [58].…”

Section: Wall Injectionmentioning

confidence: 88%

“…Various numerical and experimental studies have been performed on fuel injection through orifices with sharp leading edges, such as diamond or wedge shaped orifice [58][59][60]. Timioka, et al [58], performed experimental studies of the plume formed by sonic injection from a diamond-shaped orifice into a Mach 3 crossflow.…”

Section: Wall Injectionmentioning

confidence: 99%

“…Timioka, et al [58], performed experimental studies of the plume formed by sonic injection from a diamond-shaped orifice into a Mach 3 crossflow. It was concluded that, at lower jet-tofreestream dynamic pressure ratio, the fuel jet penetration was higher from a diamond-shaped orifice as compared to an equivalent circular injector.…”

Section: Wall Injectionmentioning

confidence: 99%

See 2 more Smart Citations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Section: Wall Injectionmentioning

confidence: 88%

Section: Wall Injectionmentioning

confidence: 99%

See 1 more Smart Citation

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…To accelerate the development of coherent structures, a velocity fluctuation field obtained from a previous LES/RANS simulation of a Mach 3 boundary layer at a Reynolds number / meter of 49.5e6 [25] was superimposed upon the RANS base state upstream of the wedge apex. The Mach 3 velocity fluctuation field was expanded in the periodic Z (spanwise) and assumed periodic X (streamwise) directions to cover the X-Z extent of the flat-plate region.…”

Section: Initialization Procedures and Time Evolution Detailsmentioning

confidence: 99%

Simulation of Transient Dynamics of Shock Wave Boundary Layer Interactions Using Hybrid Large-Eddy/Reynolds-Averaged Navier-Stokes Models

Edwards¹

2007

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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 comment regarding this burden estimates or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and 49624.1-EG-IISimulations of the Mach 5 compression-corner shock / turbulent boundary layer interaction experimentally mapped by Prof. David Dolling and co-workers have been performed using a hybrid large-eddy / Reynolds-averaged Navier-Stokes (LES/RANS) model. The model captures the mean-flow structure of the interaction reasonably well, with observed deficiencies traced to an underprediction of the displacement effects of the shock-induced separation region. The computational results provide some support for a recent theory relating to the underlying causes of low-frequency shock wave oscillation. The simulation results indicate that the sustained presence of a collection of neighboring streaks of low / high momentum fluid within the boundary layer induces a lowfrequency undulation of the separation front. Power spectra obtained at various streamwise stations are in good agreement with experimental results, indicating that the LES/RANS method is capable of predicting both the low and high-frequency dynamics of the interaction. Downstream of re-attachment, the simulations capture a three-dimensional mean flow structure, dominated by counter-rotating vortices that produce wide variations in the surface skin friction. Predictions of the structure of the re-attaching boundary layer agree well with experimental pitot pressure measurements. In comparison with Reynolds-averaged model predictions, the LES/RANS model predicts more amplification of Reynolds stresses and a broadening of the Reynolds-stress distribution within the boundary layer that is probably due to re-attachment shock motion.40 hybrid large-eddy / Reynolds-averaged Navier-Stokes simulations, shock wave / turbulent boundary layer interaction, shock system dynamics Project Abstract (Original Proposal)Many experimental investigations have noted that complex shock / boundary layer interactions exhibit large-scale, low frequency motion that is distinct from that associated from wall-layer turbulence. This motion results in fluctuating pressure and heat-transfer loads that can adversely affect the performance of supersonic missile systems, among others. Accurate predictions of such effects would appear to require a time-dependent modeling strategy, such as large-eddy simulation (LES) or direct numerical simulation (DNS). The application of these techniques to flows at practical Reynolds numbers requires immense computational resources, and as yet, very few studies have...

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“…Jet injection into supersonic cross flows has applications in flow control, creation of forces and moments for attitude control, and most importantly in scramjets for supersonic combustion to take place [1][2][3][4][5][6][7][8][9]. Mai et al [10] showed that by having an incident shock impinge downstream of a transverse jet injection location, enhanced mixing of the fuel and air can be achieved leading to increased residence time and more efficient combustion.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Impinging Shock – Cavity Interactions with Upstream Transverse Jet Injection

Zare‐Behtash

Ukai

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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Sonic Injection from Diamond-Shaped Orifices into a Supersonic Crossflow

Cited by 72 publications

References 14 publications

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Simulation of Transient Dynamics of Shock Wave Boundary Layer Interactions Using Hybrid Large-Eddy/Reynolds-Averaged Navier-Stokes Models

Experimental Investigation of Impinging Shock – Cavity Interactions with Upstream Transverse Jet Injection

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