Flow field characteristics of a supersonic jet influenced by downstream microjet fluidic injection

Pourhashem, Hamideh; Kumar, Sunil; Kalkhoran, Iraj M.

doi:10.1016/j.ast.2019.07.014

Cited by 13 publications

(4 citation statements)

References 44 publications

(79 reference statements)

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“…This interaction is discussed here with a focus on noise creation and reduction when a jet is parallel to or impinging on a solid wall. Various researchers have presented computational methods [65,66] with large-eddy simulations [67][68][69][70][71], high fidelity simulations [72] and 3D simulation [73]. The noise reduction of supersonic jets by nozzle trailing-edge changes was investigated experimentally [74], and hemispherical noise reduction reflectors on transonic jet flows [75] were conducted.…”

Section: Noise Controlmentioning

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: Noise Controlmentioning

confidence: 99%

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

2021

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“…In terms of active noise control technology, some scholars also use microjet technology to reduce noise. The constriction effect of the microjet can significantly narrow the turbulent intensity distribution (Gza et al ,2020), and the injection of microjet can thicken the shear layer, enhance the mixing effect (Pourhashem et al , 2019) and produce a low frequency attenuation phenomenon (Castelain et al , 2006). The jet flow ratio is a key parameter, which can affect the penetration of the microjet to the core of the jet potential flow and directly affect the flow of the mainstream (Prasad and Morris, 2020).…”

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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“…Moreover, lateral jet control can effectively prevent the adverse effects of local aerodynamic heating of an air vehicle at hypersonic conditions. Compared with the conventional control rudder, an air vehicle using a lateral jet as the reaction control system can still maintain high maneuverability and low response time even in the low-density or low-speed region [3][4][5]. The lateral jet control technique has been applied in many air vehicles because of its good comprehensive performance.…”

Section: Introductionmentioning

confidence: 99%

“…In particular, the change in angle further changes the flow and produces unsteady flow. 3 When the flow around the air vehicle changes, it causes the aerodynamic forces on the air vehicle to change. 4 The original force balance state of the air vehicle is further broken, which again changes the air vehicle motion, including linear and angular motion.…”

Section: Introductionmentioning

confidence: 99%

Solving the Moment Amplification Factor of a Lateral Jet by the Unsteady Motion Experimental Method

Xue

Zhang²,

Cao

et al. 2022

Applied Sciences

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In this paper, unsteady motion tests of a lateral jet adjusting an air vehicle’s attitude are carried out. Curves of pitch moment amplification factors (KM) for a lateral jet versus angle of attack (α) are obtained using a wind tunnel free-flight test technique with a jet and data processing method. This new method overcomes the disadvantage of previous experiments that can study only one unsteady characteristic. The free-flight test technique in the proposed method ensures that the test model can be coupled in real-time with multiple parameters (unsteady flow caused by the jet, unsteady air vehicle aerodynamic force, and unsteady air vehicle motion). This approach simulates an actual air vehicle’s complete jet test process and ensures more authentic and reliable test results. In the new data processing method, continuous data curves are fitted to discrete data points, making it easier to convert the angular displacement versus time curve into the pitch moment versus α curve to obtain KM. The results show that when the pressure of the micro high-pressure gas cylinder is 2.0 MPa, KM is below 1, indicating that the lateral jet does not significantly promote the pitching moment. When the gas cylinder pressure is 4.0 MPa and the angle of attack is 5° < |α| < 16°, KM is greater than 1, and the lateral jet promotes the pitching moment. When 16° < |α| < 20°, KM is less than 1, and the lateral jet does not significantly contribute to the pitching moment. It was further found that KM decreases slowly with increasing α. When |α| > 30°, the influence of the jet on the pitching moment nearly disappears.

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Flow field characteristics of a supersonic jet influenced by downstream microjet fluidic injection

Cited by 13 publications

References 44 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

Solving the Moment Amplification Factor of a Lateral Jet by the Unsteady Motion Experimental Method

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