The flow features of Transverse Jets In Supersonic Crossflow

Zhang, Ziao; McCreton, S.; Awasthi, Manuj; Wills, Angus O.; Moreau, Danielle; Doolan, Con J.

doi:10.1016/j.ast.2021.107058

Cited by 14 publications

(4 citation statements)

References 32 publications

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“…Researchers used the flat jet as the research object and studied the change of jet flow characteristics, the structure of jet interaction flow field and pressure distribution, the characteristics of the jet shear layer, the structure of large-scale vortex, the main factors affecting jet and the problem of multi-nozzle jet interaction through experiments, and verified the numerical simulations, such as the Reynolds averaged numerical simulation (RANS), large eddy simulation (LES), detached eddy simulation (DES), and hybrid RANS/LES methods [7][8][9][10][11][12][13]. Li [14] employed the Bayesian method to recalibrate the closure coefficient of the Spalart-Allmaras (SA) turbulence model in order to improve the performance of jet interaction in supersonic and quantify the uncertainty of separation length and wall pressure.…”

Section: Introductionmentioning

confidence: 83%

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

et al. 2023

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A new idea of nosebleed air jets with strong coupled internal and external flow is put forward using the lateral jet control principle to improve the maneuverability and fast reaction capabilities of hypersonic vehicles. The hypersonic vehicle’s nose stagnant high-pressure and high-temperature gas is utilized as the drive source for long-term jet control. The significant coupled jet interaction of the internal and external flow changes the aerodynamic characteristics. As a result, the structure is basic and does not rely on any external source to achieve flight attitude control. The complicated flow characteristics of the nosebleed jet in supersonic crossflow surrounding the vehicle were numerically and experimentally investigated. The jet interaction characteristics and the aerodynamic characteristic changes generated by the nosebleed air jet are verified by comparing the flow field with and without the jet. Results indicate that the nosebleed air jet alters the center-of-pressure coefficient, which is subsequently coupled with the interference aerodynamic force. This results in a variation in pitch moment. The jet decreases the pitching moment coefficient when compared with the case without a jet. It is probable that combining nosebleed air jets with model centroid adjustment yields an optimal trim angle of attack.

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Section: Introductionmentioning

confidence: 83%

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

et al. 2023

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“…The conventional schlieren system used here to visualise the wake was recently used by Zhang et al. (2021) to study transverse jets in supersonic cross-flow and the details of this system can be found there. The schlieren videos were recorded using a monochromatic, MEMRECAM HX-7s high-speed camera.…”

Section: Experimental Set-upmentioning

confidence: 99%

“…The system is backlit using the same plasma light source as the conventional schlieren system (see Zhang et al. (2021) for a description of the conventional schlieren system), however, a Fresnel lens/source grid arrangement is placed in front of this source which then acts as the effective source of the system. The purpose of the Fresnel lens is to enhance the brightness of the system.…”

Section: Experimental Set-upmentioning

confidence: 99%

Supersonic cylinder wake dynamics

et al. 2022

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The supersonic wake of a circular cylinder in Mach 3 flow was studied through high-speed, focussing schlieren photography. The mean and unsteady behaviour of the separated shear layers, the reattachment process, the recompression wave and the early wake are analysed, and discussed in detail. The fluctuations in the wake are stronger and more coherent than those within the approaching shear layers and the recirculation region. The recompression of the shear layers energises the finer scales in the flow which leads to a departure from a $-$ 1 spectral roll-off observed in the schlieren spectra further upstream. The recompression wave exhibits low-frequency unsteadiness and a ripple-type motion which occurs as it is perturbed by shocklets radiating from the coherent structures in the wake. The wake consists of coherent disturbances with the same characteristic frequency as that for an incompressible flow over a cylinder; however, this instability is suppressed as the wake accelerates, presumably due to increasing compressibility. The primary instability of the wake flow has a characteristic frequency nearly twice that of its incompressible counterpart and it is shown to be driven by the presence of aeroacoustic resonance in the wake. It is also shown that the resonance, which leads to the formation of broadband standing waves in the wake, is the result of an interaction between the wake instabilities and upstream propagating acoustic waves in the wake. The acoustic waves originate upstream of the reattachment region and are believed to be generated by the unsteady separation on the cylinder surface.

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“…The mechanism of the shock wave and vortices structures, which increases the mixing layer, has been studied from the point of view of the steady flow in ref. [12] and the unsteady flow physics [13,14]. However, in this investigation the JICF problem was solved as a rule with significant simplification of simulation, such as the symmetrically jet injections, study of the regions of jet injection.…”

Section: Introductionmentioning

confidence: 99%

Simulation of the shock wave boundary layer interaction in flat channel with jet injection

et al. 2023

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The improvement of the mixing of the injected jet fuel in the cross‐flow oxidant (jet in cross‐flow (JICF)) in the scramjet combustor is still remains opened problem. JICF is accompanied with the formation of shock structures and leads to the shock wave boundary layer interactions (SWBLI) at the walls of the combustion chamber. The purpose of this paper is to study the influence of the interaction of the bow shock wave with the upper boundary layer and shock wave (reflected from the upper wall) with lower surface flow behind the jet on the mixture layer mechanism. For that, the numerical simulation of a supersonic flow with a transverse multispecies jet injection from the bottom wall of the plane channel with variations of the channel heights and the jet pressure ratio is done. The multispecies supersonic gas flow in a planar channel with perpendicular jet injection is numerically simulated. The Favre‐averaged Navier‐Stokes equations coupled with the k‐ω turbulence model are solved using the fourth order weighted essentially non‐oscillatory (WENO)‐scheme. The simulation correctly captured the main flow features near the jet and the comparison with the experimental data shows a satisfactory agreement. The reflected shock wave, formed as a result of the interaction of a bow shock wave with the boundary layer (SWBLI), reaches the lower boundary layer behind the jet and interacts with them. The numerical experiments reveal show that this shock/wave interaction causes an oscillation of the flow. The channel height variations show that with a decrease of the height the mixing rate increased.

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The flow features of Transverse Jets In Supersonic Crossflow

Cited by 14 publications

References 32 publications

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

Supersonic cylinder wake dynamics

Simulation of the shock wave boundary layer interaction in flat channel with jet injection

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