Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Wang, Yangsheng; Xu, Jianzhong; Huang, Shuai; Lin, Yong-Chen; Jiang, Jintao

doi:10.1177/0954410019872089

Cited by 20 publications

(7 citation statements)

References 26 publications

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“…They have been used in many real supersonic fighters, such as F-22 Raptor, F-15S/MTD, and SU-27 Flanker. Wang et al (2019b) experimentally confirmed the real flow features in the conical DTN are not fully axisymmetric based on oil flow visualization technology. It is not well demonstrated that if this asymmetric flow characteristic would occur in a 3-D rectangular DTN.…”

Section: Fig 1 Illustration Of Aircraft Axessupporting

confidence: 53%

“…All nozzle and slot injection syringe surfaces are assumed as adiabatic walls. Other exit boundaries are taken as the pressure outlet boundary.All current CFD work is finished in the software of Fluent that is good at calculating incompressible and compressible flows based on pressure-based and density-based solvers(Lin et al 2020;Tao et al 2020;Wang et al 2019a;Wang et al 2019b). By referring to earlier references(Deng and Kim 2015;Vignesh et al 2016;Vignesh et al 2019;Wu and Kim 2019a;Raman et al 2020;Wu et al 2020a), the density-based solver is fixed for issues of compressible flow.…”

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confidence: 99%

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Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

2021

JAFM

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Compared to a variety of mechanical vectoring nozzles, fluidic vectoring nozzles possess more research value nowadays. The dual throat nozzle is gradually developing into an outstanding technology to handle supersonic and hypersonic aircraft deflections. Three-dimensional, steady, compressible, and viscous flows in rectangular dual throat nozzles are numerically investigated by resolving Reynolds-averaged Navier-Stokes equations and shear stress transport k-omega turbulence model. Computational fluid dynamics results are verified against the existing experimental data, where a good consistency is gained. The impacts of nozzle pressure ratio, injection-to-mainstream momentum flux ratio, and setup angle of the slot injector on the systemic performance are examined. Useful conclusions are summarized for engineering designers. Firstly, pitching angles decline along with an increasing nozzle pressure ratio, while systemic thrust ratio and thrust efficiency increase. Secondly, thrust vector angles enlarge with an increase of the injection-to-mainstream momentum flux ratio, whereas both systemic thrust ratio and thrust efficiency decay. Finally, the setup angle of the slot injector impacts the systemic performance remarkably. Although the pitching angle for the setup angle of 120° is highest, comprehensive characteristics in terms of systemic thrust efficiency and systemic thrust ratio for the setup angle of 150° are more excellent.

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Section: Fig 1 Illustration Of Aircraft Axessupporting

confidence: 53%

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confidence: 99%

Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

2021

JAFM

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“…11,34,35 Also several numerical investigations about BDTN or conventional DTN flows have used the same boundary conditions. 12,13,16,17…”

Section: Methodsmentioning

confidence: 99%

“…Also Wang et al. 17 prove that the actual flow in the axisymmetric divergent dual throat nozzle (ADDTN) indeed possesses three-dimensional characteristics by comparing the flow structure, nozzle surface static pressure distributions and skin friction lines, which are obtained by numerical simulations and wind tunnel experiments.…”

Section: Introductionmentioning

confidence: 99%

Experimental evaluation and numerical simulation of performance of the bypass dual throat nozzle

Hamedi-Estakhrsar

Mahdavy-Moghaddam

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Bypass dual throat nozzle (BDTN) is a modern concept of fluidic thrust vector control. This method able to solve the problem of thrust loss without need the secondary mass flow from other part of engine. Internal nozzle performance and thrust vector angles have been measured in the BDTN experimentally and numerically. A new simple approach is proposed to detect the thrust deflection angle. Numerical simulation of 3-D turbulent air flow is carried out by using the RNG k-e turbulence model. The obtained results of thrust coefficient, discharge coefficient and thrust deflection angle have been validated by comparing with measured experimental data. The results show that for nozzle pressure ratio of 1–4 the tested nozzle able to deflect the thrust vector of 26.5°-19°. By increasing NPR from 2 up to 4, the thrust coefficient values will change in the range of 0.85-0.93. Also the effect of different positions of the bypass channel on the BDTN performance parameters has been investigated numerically. The predicted results show that the BDTN configuration with bypass duct on the first nozzle throat has the highest value of thrust deflection angle over the range of NPRs.

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“…The standard ambient pressure is kept constant at 101325 Pa. The stagnation temperatures of the injected and primary streams have a constant value of 297.04 K. In past validation studies, Wang et al [22] attempted to validate their numerical research methodology with the Spalart-Allmaras, realizable k-epsilon (kε), and SST k-ω turbulence models and elaborated on that the SST k-ω turbulence model gives the best accuracy in agreement with the experimental result. Consequently, the SST k-ω turbulence model is performed to verify our present research methodology.…”

Section: Experimental Verificationmentioning

confidence: 99%

A fluidic thrust vector control using the bypass flow in a dual throat nozzle

Kim

2021

J Mech Sci Technol

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The present study is to explore an active mass flow control technology for an emerging bypass dual throat nozzle. A new arc-shaped bypass system has been applied to replace the previous V-shaped bypass for the bypass dual throat nozzle, which can decrease the total pressure loss significantly. The bypass passage has a contraction part with a variable area ratio. The vector control effectiveness is discussed with different contraction area ratios of the bypass passage. The obtained results reveal that friction choking and geometry choking play crucial roles to affect the bypass mass flow, respectively. When the bypass passage is fully open, the choking location of the bypass flow occurs at the bypass exit, owing to the viscous boundary layer along the constant area passage. A contraction area ratio less than 0.5 does not change the choking position of the bypass flow, because the viscous boundary layer is larger than the geometry contraction height. While the contraction area ratio reaches or exceeds 0.5, the geometry choking takes place in the contraction section. The vectoring angle and bypass mass flow ratio decrease with an increase in the contraction area ratio, whereas thrust coefficient, thrust efficiency, and total pressure loss increase.

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Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Cited by 20 publications

References 26 publications

Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

Experimental evaluation and numerical simulation of performance of the bypass dual throat nozzle

A fluidic thrust vector control using the bypass flow in a dual throat nozzle

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