Experimental and numerical research of a supersonic planar thrust vectoring nozzle via mechanical tabs

Živković, Sanja; Milinović, Momčilo; Adamec, N.

doi:10.5937/fmet1403205z

Cited by 12 publications

(7 citation statements)

References 6 publications

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“…In such cases, active flow control has an increasing potential to bring a range of benefitsin terms of airframe weight reduction, lift increase, drag, and noise reductions, and has become an essential component in aircraft design [5]. In addition to aerodynamic improvements, active flow control is increasingly interesting in a myriad of other applications, such as: control of boundary layers in wind tunnels [6], smoke propagation [7], flows around hydrodynamic surfaces [8], noise reduction [9], flows around miniature UAVs [10][11][12], separated flows in supersonic nozzles [13], or thrust vectoring [14], just to name a few.…”

Section: Introductionmentioning

confidence: 99%

On the impact of geometry scaling and mass flow rate on the frequency of a sweeping jet actuator

Slupski¹,

Tajik²,

Parezanović³

et al. 2019

FME Transactions

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This paper presents an experimental and numerical study of the sweeping jet oscillation frequency which is a crucial parameter for effective separation control. Measurements of the time-resolved static pressure are made in the feedback channels using high-frequency pressure transducers. Experiments are performed for eight different inlet mass flow rates (from 1g/s to 8 g/s). The effects of geometry scaling are examined for the halfand double-size of the baseline actuator. The results reveal a relationship between the oscillating frequency and the inlet mass flow rate and demonstrate a linear trend of the Strouhal number versus the inlet Mach number for all the geometries. The experimental results are compared toresults obtained from numerical simulations using Ansys Fluent v17.2 software.A high correspondence is found between experimental results and numerical data from computationally inexpensive 2D-URANS simulations. This result opens possibilities of using these simple numerical models to perform extensive studies of the geometric parameters of the sweeping jet actuator in the future.

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Section: Introductionmentioning

confidence: 99%

On the impact of geometry scaling and mass flow rate on the frequency of a sweeping jet actuator

Slupski¹,

Tajik²,

Parezanović³

et al. 2019

FME Transactions

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“…(Also, very interesting CFD analyses, using higher order turbulence models than in this paper, considering the same experiments [1], but with exit Mach number M = 2.3 and 10% shadowing tab, can be found in Živković at al. [13]. )…”

Section: Cfd Analysis Of Jet Tabs and Comparisons With The Experimentmentioning

confidence: 98%

Comparative CFD analysis of a 2D supersonic nozzle flow with jet tab and jet vane

2017

Teh. vjesn.

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Original scientific paper In this study, a CFD (Computational Fluid Dynamics) computational model has been established, with the aim to properly simulate complex supersonic flow generated by a 2D convergent-divergent nozzle. For the purpose of rocket engine thrust vector control (TVC) simulations, initially several jet tab positions were used to generate up to 30% shadowing of the nozzle exit, without and with a gap between tab and exit. Numerical results were compared with the existing experimental data, both quantitatively and qualitatively, and fair agreements have been obtained in both senses. The same CFD settings have then been applied for the computational analysis of another TVC type -the jet vane, which was analysed in four different adopted configurations with respect to the nozzle. Stable convergence of solutions has been achieved, up to 40° of vane deflections. Performed calculations have enabled comparisons of the two considered TVC types, in the sense of the achieved thrust force deflections, and thrust losses. Keywords: CFD analysis; flow visualization; jet tab; jet vane; supersonic nozzle; thrust vector control Usporedna CFD analiza 2D strujanja supersoničnog mlaznika sa spojlerom i s mlaznim krilcemIzvorni znanstveni članak U okviru ove studije, ustanovljen je CFD (Computational Fluid Dynamics) proračunski model za potrebe analize kompleksnog nadzvučnog strujnog polja generiranog 2D konvergentno-divergentnim mlaznikom. U cilju simulacije upravljanja vektorom potiska (UVP) raketnih motora, najprije je rabljen spojler, postavljen u nekoliko položaja do maksimalnih 30% zasjenčenja površine izlaznog presjeka, bez procjepa i s procjepom u odnosu na izlaz. Proračunski rezultati uspoređeni su s raspoloživim eksperimentalnim rezultatima kvantitativno i kvalitativno, pri čemu su u oba slučaja dobivena zadovoljavajuća

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“…The plateau pressure, which is the mean pressure in the recirculation zone, was also studied. Živković et al . (2014), performed numerical and experimental studies to obtain the pressure distribution, recirculation zone characteristics, shock wave characteristics and influence of gap between tab and nozzle exit using mechanical tabs in a supersonic planar thrust vectoring nozzle.…”

Section: Literature Backgroundmentioning

confidence: 99%

Study of jet tabs in 2D convergent–divergent nozzle for thrust vectoring in aerial vehicles

Jyothy

Wessley

2023

IJIUS

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PurposeIn this study, 2D density-based SST K-turbulence model with compressibility effect is used to observe the flow separation and shock wave interactions of the flow. The wall static pressure and Mach number differences are also evaluated. This study aims to discuss the aforementioned objectivesDesign/methodology/approachThis study outlines the evaluation of the performance of a 2D convergent–divergent nozzle with various triangular jet tab configurations that can be used for effective thrust vectoring of aerial vehicles.FindingsFrom the study, it is seen that the shadow effect induced by the tab with a height of 30% produces higher oblique wave deflection and higher thrust deflection at the exit nozzle. The numerical calculation concluded that thrust vector efficiency of 30% jet tab is, 0.46%. In the case of 10% jet tab height the thrust vector efficiency is higher, i.e. 1.647%.Research limitations/implications2D study.Practical implicationsThe optimization will open up a new focus in TVC that can be implemented for effective attitude control in aircrafts.Social implicationsUsed in future aircrafts.Originality/valueThe influence of shadowing ratio with different tab heights at different Mach numbers has not been reported in the previous studies. Few of the studies on jet tab are focused on the acoustic studies and not pertaining to the aerodynamic aspects. The multi jet configuration, the combination of location, shapes and other parametric analysis have not been covered in the previous studied.

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Experimental and numerical research of a supersonic planar thrust vectoring nozzle via mechanical tabs

Cited by 12 publications

References 6 publications

On the impact of geometry scaling and mass flow rate on the frequency of a sweeping jet actuator

On the impact of geometry scaling and mass flow rate on the frequency of a sweeping jet actuator

Comparative CFD analysis of a 2D supersonic nozzle flow with jet tab and jet vane

Study of jet tabs in 2D convergent–divergent nozzle for thrust vectoring in aerial vehicles

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