Numerical simulation of fluidic thrust vectoring in an axisymmetric supersonic nozzle

Deng, Ruoyu; Kong, Fanshi; Kim, Heuy Dong

doi:10.1007/s12206-014-1119-x

Cited by 40 publications

(18 citation statements)

References 8 publications

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“…Nowadays, there are many researches on the steering device of the waterjet propulsion system [15,18]. e fluidic thrust vector control technologies in the aviation field also provides a new research direction for the reversing device of waterjet propulsion [19,20].…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of Inlet Passage for Waterjet Propulsion System Based on Flow and Geometric Parameters

Jiao

Cheng

Zhang

et al. 2019

Advances in Materials Science and Engineering

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As an important overcurrent component in a waterjet propulsion system, the inlet passage is used to connect the propulsion pump and the bottom of the propulsion ship. e anticavitation, vibration, and noise performance of the waterjet propulsion pump are significantly affected by the hydraulic performance of the inlet passage. e hydraulic performance of the inlet passage directly affects the overall performance of the waterjet propulsion system, thus the design and optimization method of the inlet passage is an important part of the hydraulic optimization of the waterjet propulsion system. In this study, the hydraulic characteristics of the inlet passage in the waterjet propulsion system with different flow parameters and geometric parameters were studied by a combination of numerical simulation and experimental verification. e model test was used to verify the hydraulic characteristics of the waterjet propulsion system, and the results show that the numerical results are in good agreement with the test results. e numerical results are reliable. e hydraulic performance of the inlet passage is significantly affected by the inlet velocity ratio.ere is a certain correlation between the hydraulic performance of the inlet passage and ship speed, and the hydraulic performance of the inlet passage is limited by ship speed. e geometric parameters of the best optimization case are as follows: the inflow dip angle α is 35°, the length L is 6.38D 0 , and the upper lip angle is 4°. e optimal operating conditions are the conditions of IVR 0.69-0.87.

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Section: Introductionmentioning

confidence: 99%

Optimal Design of Inlet Passage for Waterjet Propulsion System Based on Flow and Geometric Parameters

Jiao

Cheng

Zhang

et al. 2019

Advances in Materials Science and Engineering

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“…The momentum flux ratio J is an important parameter in determining the separation distance and the depth of penetration of a jet in cross flow as in eqn. (13) [11,29]. J increases as the injection location moves downstream, as shown in Table 3, leading to increasing penetration depth and the separation distance upstream the injection…”

Section: Influence Of Injection Locationmentioning

confidence: 99%

“…Sellam et al [5] analyzed the thermodynamic characteristics of the injected gas on FTV performance. Deng et al [29] established an analytical model for transverse injection and performed a numerical model for secondary injection to study the thrust vectoring efficiency and system thrust ratio. Erdem and Kontis [30] carried out numerical simulations and experiments to analyze the transverse injection, then Erdem et al [31] investigated experimentally the penetration characteristics of the transverse sonic jets in Mach 5 cross flows for air, carbon dioxide, and helium.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation on the Influence of Injection Location, Injection Angle, and Divergence Half Angle on SITVC Nozzle Flow Field

Noaman

Khalil

2019

International Journal of Aerospace Engineering

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A numerical study has been performed to characterize the nozzle flow field of secondary injection thrust vector control (SITVC) and to estimate the performance parameters of SITVC. After validating the CFD turbulence models with an experimental data, a numerical simulation has been conducted in order to investigate the influence of changing the injection location, the injection angle, and the primary nozzle divergence half angle on the SITVC nozzle flow field structure and on the SITVC performance parameters. The secondary mass flow rate was kept constant for all cases during the simulation. The results showed that downstream injection near the nozzle exit Mp=2.75 increases the high-pressure zone upstream the injection leading to an increase in the side force; also, the higher divergence half angle 15° slightly increases the side force and it provides a wide range of deflection without shock impingement on the opposite wall becoming more effective for SITVC. The injection angle in the upstream direction 135° increases the side force, and by decreasing the injection angle to downstream direction 45°, the side force decreases. However, the SITVC performance parameters and the flow field structure are more influenced by the injection location and the primary nozzle divergence half angle while being less influenced by the injection angle.

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“…For an injector (at an NPR = 4.6 and a SPR = 0.7), the results obtained show a strong influence of the ambient pressure prevailing downstream of the injector and the thrust vector angle obtained is around 7°. In 2014, Deng et al, [7] proposed an analytical model to study the depth penetration and the pressure distribution for the injector. The results obtained were adequate with experimental data.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Fluidic Thrust Vectoring in the Conical Nozzle

Hakim

Toufik

Bergheul

2020

ARFMTS

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The application of fluid injection into the divergent portion of a supersonic nozzle to release the pushed vector is an attractive alternate to conventional thrust vectoring systems. Indeed, it can replace mechanical complexes. In recent years, this new thrust vectoring technology is the subject of numerous experimental and numerical researches, and has allowed countless applications due to its many advantages. A thrust vectoring concept is currently being applied to new-generation fighter aircraft equipped with jet engine. Fluidic thrust vectoring also finds application in satellite altitude control systems; this principle reduces the number of nozzles used. This study is based on ANSYS-FLUENT and analyzes the different phenomena involved. The results of thrust vectoring performances (angle of deviation, efficiency, lateral forces, etc.) are compared to those in the bibliography.

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Numerical simulation of fluidic thrust vectoring in an axisymmetric supersonic nozzle

Cited by 40 publications

References 8 publications

Optimal Design of Inlet Passage for Waterjet Propulsion System Based on Flow and Geometric Parameters

Optimal Design of Inlet Passage for Waterjet Propulsion System Based on Flow and Geometric Parameters

Numerical Simulation on the Influence of Injection Location, Injection Angle, and Divergence Half Angle on SITVC Nozzle Flow Field

Numerical Simulation of Fluidic Thrust Vectoring in the Conical Nozzle

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