Performance of corrugated actuator-tabs of aspect ratio 2.0 on supersonic jet mixing enhancement

Jana, Tamal; Kaushik, Mrinal

doi:10.1007/s12206-021-0222-z

Cited by 6 publications

(3 citation statements)

References 18 publications

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“…The centerline pressure plot for the plain actuator and the rectangular, semicircular, and triangular tabs of aspect ratio 1.5 is shown in Figure 8, where the pressure decay for the triangular corrugated tab is maximum at the near correct expansion condition. The subsequent study of Jana and Kaushik [35], with the deployment of tabs of different corrugation shapes of aspect ratio 2, revealed that the core length decrement is maximum for rectangular tab at overexpansion conditions. However, the triangular and semicircular corrugated tab is the most effective in jet mixing in the far-field.…”

Section: Supersonic Jet Controlled With Tabsmentioning

confidence: 97%

Survey on Vortex Shedding Tabs as Supersonic Jet Control

et al. 2022

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This study provides an overview of the tab-controlled jets to understand and predict the influence of mixing promoting vortices at speeds ranging from subsonic to supersonic. A detailed description of various features of the circular jets controlled by tab-like vortex generators is provided. Here, both the experimental and the numerical investigations on the impacts of tabs on the mixing enhancement and noise suppression are presented. Following a brief introduction about subsonic and supersonic circular jets, this study discusses the influences of certain key parameters on mixing characteristics, including the effect of tab geometry, tab number, tab orientation, tab size, and tab position relative to nozzle outlet. Subsequently, their effect on noise suppression is also reviewed. The detrimental effect of tabs in terms of thrust penalty is described. Finally, the future direction of research on the tab-controlled jets is outlined.

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Section: Supersonic Jet Controlled With Tabsmentioning

confidence: 97%

Survey on Vortex Shedding Tabs as Supersonic Jet Control

et al. 2022

Self Cite

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“…Modification of shape in corrugations of tab was carried by Jana and Kaushik (2021), in which the rectangular, triangular and semicircular shape corrugations were investigated for the exit jet Mach number 1.73. Supersonic Jet core shocks were weakened by the corrugated tabs efficiently than plain tabs (Chiranjeevi and Rathakrishnan, 2010).…”

Section: Introductionmentioning

confidence: 99%

Investigation of slanted perforation diameter in tabs for supersonic jet control

Ezhilmaran¹,

Sekar²,

K.³

et al. 2023

AEAT

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Purpose This study aims to investigate the effect of slanted perforation diameter in tabs for the control of Mach 1.4 underexpanded supersonic jet flow characteristics. Design/methodology/approach Numerical investigation was carried out for NPR 5 to analyze the effect of slanted perforation diameter in tabs to control the Mach 1.4 jet. Four sets of tabs with slanted circular perforation geometries (Φp = 1, 1.5, 2 and 2.5 mm) were considered in this study. The inclination angle of 20° (αP) with reference to the jet axis was maintained constant for all the four tabs considered. Findings Determined value indicates there is a 68%, 71%, 73% and 75% drop in supersonic core for the Φp = 1, 1.5, 2.0 and 2.5 mm, respectively. The results show that the tabs with 2.5 mm perforation diameter were found to be efficient in reducing the supersonic jet core in comparison with other tab cases. The reduction in supersonic core length is due to the extent of miniscule vortices exuviating from slanted small and large diameter perforation in the tabs. Practical implications The concept of slanted perforation can be applied in scramjet combustion, which finds its best application in hypersonic vehicles and in noise suppression in fighter aircraft. Originality/value Slanted perforation and circular shapes with different diameters have not been studied in the supersonic regime. Examining the effect of circular diameter in slanted perforation is an innovation in this research paper.

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“…This is due to the local shock waves generated by the grooves (Ilakkiya and Sridhar 2018). The presence of tabs in a supersonic jet, on the other hand, causes the jet to split along the tab orientation, meanwhile, the jet merges in the direction normal to the tab (Jana and Kaushik 2021). Besides, the nozzles having different shapes other than an axisymmetric nozzle may have different flow topologies in different plane directions (Lee et al 2012).…”

Section: Introductionmentioning

confidence: 99%

Shock-Structure Formation in Circular and Non-Circular Sonic Jets at Underexpanded Conditions

2022

JAFM

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The generation of shock waves and their repercussions in high-speed vehicles are inevitable. Particularly, the hot plume from the aircraft exhaust ejecting at a high speed, as well as the emitted aeroacoustic noise, have several consequences. Besides, the occurrence of the supersonic core length and the emission of high screech noise are mostly due to the shock cells, prevailing in high-speed jets. Therefore, understanding the shock cell structures developed at the exit of aircraft or rocket nozzles is vital in improving mixing and thereby the noise characteristics. Essentially, non-circular nozzle shapes are well known for enhancing entrainment characteristics and mitigating the noise due to their differential spreading over the nozzle's perimeter. The current study examines the shock structures of circular, elliptic, and square jets at various sonic underexpansion levels. In this investigation, the nozzle geometries are considered to have the same exit area. The Nozzle Pressure Ratio (NPR) was adjusted to 3, 4, and 5 to achieve moderate and highly underexpansion conditions. The shadowgraph visualization method is used to study the development of shock cells from axisymmetric and asymmetric nozzles. It is interesting to observe that the incident and reflected shock structures exist only at moderate and high underexpansion levels. Besides, the elliptic and the square jets have distinctive flow patterns along their different axis planes. The intercepting shock appears on the elliptic jet in the minor axis rather than the major axis direction. The curvature of the intercepting shock wave was found to be greater for the elliptic jet than that for the circular jet. In addition, the square jet in the symmetry plane diverges from the jet centerline, but the jet in the diagonal direction converges. Moreover, the estimated shock cell lengths using shadowgraph images were compared to a theoretical model where the experimentally obtained results are in good agreement with the theoretical values.

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Performance of corrugated actuator-tabs of aspect ratio 2.0 on supersonic jet mixing enhancement

Cited by 6 publications

References 18 publications

Survey on Vortex Shedding Tabs as Supersonic Jet Control

Survey on Vortex Shedding Tabs as Supersonic Jet Control

Investigation of slanted perforation diameter in tabs for supersonic jet control

Shock-Structure Formation in Circular and Non-Circular Sonic Jets at Underexpanded Conditions

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