Numerical investigation on splitter plate jet assisted mixing in supersonic flow

Zhang, Dongdong; Tan, Jianrong; Yao, Xiao

doi:10.1016/j.actaastro.2021.06.022

Cited by 5 publications

(3 citation statements)

References 38 publications

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“…It contains many computer models, including experimental system architecture, fuzzy set theory, neural networks, and approximate reasoning, and it requires intensive computing for learning and reworking. The CFD procedure also used to explore the flow through the wedge [138,139], noncircular cylinder [137,140], splitter plate [141][142][143], airfoil [144,145] and powered submarine [146] for an incompressible flow range. From the fluent, more studies were found in recent years in which some studies have been utilized with the pressure-based solver, and K-epsilon turbulent modeling was used [134,136].…”

Section: Soft Computing Methodsmentioning

confidence: 99%

A Critical Review of Supersonic Flow Control for High-Speed Applications

2021

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In high-speed fluid dynamics, base pressure controls find many engineering applications, such as in the automobile and defense industries. Several studies have been reported on flow control with sudden expansion duct. Passive control was found to be more beneficial in the last four decades and is used in devices such as cavities, ribs, aerospikes, etc., but these need additional control mechanics and objects to control the flow. Therefore, in the last two decades, the active control method has been used via a microjet controller at the base region of the suddenly expanded duct of the convergent–divergent (CD) nozzle to control the flow, which was found to be a cost-efficient and energy-saving method. Hence, in this paper, a systemic literature review is conducted to investigate the research gap by reviewing the exhaustive work on the active control of high-speed aerodynamic flows from the nozzle as the major focus. Additionally, a basic idea about the nozzle and its configuration is discussed, and the passive control method for the control of flow, jet and noise are represented in order to investigate the existing contributions in supersonic speed applications. A critical review of the last two decades considering the challenges and limitations in this field is expressed. As a contribution, some major and minor gaps are introduced, and we plot the research trends in this field. As a result, this review can serve as guidance and an opportunity for scholars who want to use an active control approach via microjets for supersonic flow problems.

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Section: Soft Computing Methodsmentioning

confidence: 99%

A Critical Review of Supersonic Flow Control for High-Speed Applications

2021

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“…Among the aeroengine noise reduction methods, the enhanced mixing method of jet flow and external gas is usually used (Zhang et al , 2021a), and the sawtooth trailing nozzle is often used to achieve passive noise control, which can reduce the axial velocity and turbulent kinetic energy downstream of the jet, destroys the circumferential correlation of vortices and accelerates vortex diffusion (Yu et al , 2019; Zhang et al , 2021b). Under different jet conditions, the sawtooth length has little effect on the flow field and sound field, while the penetration rate has a large effect on high-frequency and low-frequency noise (Bridges and Brown, 2004).…”

Section: Introductionmentioning

confidence: 99%

Research on jet noise characteristics of aeroengine double S-bend nozzles with different cross sections

Shao

Zheng

et al. 2022

HFF

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Purpose This study aims to improve the survivability and maneuverability of the fighter,and study the stealth performance of fighter in the jet noise of aeroengine, it is of great significance to study the jet noise characteristics of double S-bend nozzles. Design/methodology/approach The multiparameter coupling and super-ellipse design methods are used to design the cross section of double S-bend nozzle. Taking unsteady flow information as the equivalent sound source, the noise signal at the far-field monitoring points were calculated with Ffowcs Williams–Hawkings (FW–H) method, and then, the sound source characteristics of the double S-bend nozzle are analyzed. Findings The results show that the internal flow of the S-bend nozzle with rectangular section is smoothed and the aerodynamic performance is better than super-ellipse section, the shear layer length of rectangular section is longer, the thickness is smaller and the mixing ability is stronger. The sound pressure level of the two S-bend nozzles decreases with the increase of the monitoring angle, and the sound pressure on the horizontal plane is greater than the vertical plane. In the direction of 40°–120°, the jet noise of rectangular nozzle is smaller, and the multiparameter coupled rectangular cross section structure is more applicable. Practical implications It is beneficial to reduce the jet noise of the engine tail nozzle and improve the stealth performance of the aircraft. Originality/value There is very little research on the jet noise characteristics of the double S-bend nozzle. The multiparameter coupling and the super-ellipse method are used to design the nozzle flow section to study the aerodynamic performance and jet noise characteristics of the double S-bend nozzle and to improve the acoustic stealth characteristics of the aircraft.

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“…Convective Mach number (Mc), proposed by Papamoschou et al [3], is to evaluate the compressibility effects on mixing layer. Zhang et al numerically investigated the mixing process, structural topology properties, combustion characteristics and growth rate of the supersonic mixing layer under different inflow conditions and mixing enhancing strategies using direct numerical simulation [4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on fluid characteristics of supersonic mixing layers with splitter plate in a confined space

et al. 2022

J. Phys.: Conf. Ser.

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High-speed airbreathing engines has been going on for more than a century, since French engineer Reina Lauren first developed the concept of the ramjet. Kelvin-Helmholtz (K-H) instability and compressibility effects on the evolution of supersonic mixing layer growing rate have been widely investigated in experimental and computational ways. The present study proposed a quasi-DNS solver which is written in Fortran 90, the mixing process of the supersonic planar mixing layers is analyzed in detail, especially, the process of the vortex rolling up, stretching, pairing and merging are also reported in present study. It is noteworthy that the mechanisms of K-H instability are analysed in detail, and the baroclinic term has a great influence on the growth of the supersonic mixing layer in confined space.

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Numerical investigation on splitter plate jet assisted mixing in supersonic flow

Cited by 5 publications

References 38 publications

A Critical Review of Supersonic Flow Control for High-Speed Applications

A Critical Review of Supersonic Flow Control for High-Speed Applications

Research on jet noise characteristics of aeroengine double S-bend nozzles with different cross sections

Numerical investigation on fluid characteristics of supersonic mixing layers with splitter plate in a confined space

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