Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Liu, Rubing; Niu, Zhongguo; Wang, Mengmeng; Hao, Ming; Lin, Qi

doi:10.1007/s11431-015-5881-5

Cited by 24 publications

(9 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…7. The control effect of conventional actuation is similar to the increase in the stall angle of the NACA0021 wing model by a PSJ in a previous study [10]. In addition, it is similar to the control effect of the NACA0021 wing model by a conventional synthetic jet with an injection angle of 90° adopted by Gu et al [28].…”

Section: Flow Field Comparison Under Different Actuation States At Di...supporting

confidence: 79%

“…The results showed that the drag decreased by 13% at a wind speed of 20 m/s (Re c = 6.7 × 10 5 ). Subsequently, Liu et al [10] arranged two PSJ actuators at 0.15c from the leading edge to actively control the flow separation of a NACA0021 airfoil model. The drag coefficient decreased by 33.1%, and the lift-drag ratio increased by 104.2% at a wind speed of 20 m/s (Re c = 3.6 × 10 5 ).…”

mentioning

confidence: 99%

See 1 more Smart Citation

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

et al. 2022

View full text Add to dashboard Cite

An air-supplement plasma synthetic jet (PSJ) actuator increases the air supplemental volume in the recovery stage and improves the jet energy by attaching a check valve to the chamber of a conventional actuator. To explore the flow control effect and mechanism of the air-supplement actuator, via particle image velocimetry experiments in a low-speed wind tunnel, the flow field and boundary layer characteristics of a two-dimensional airfoil surface under different actuation states were compared for different attack angles and jet orifices. The experimental results show that, compared with the conventional actuation state, the jet energy of the air-supplement PSJ is higher and the indirect mixing effect of the counter-vortex sequence produced by the jet-mainstream interaction is stronger. Furthermore, the boundary layer mixing effect is better, which can further suppress flow separation and improve the critical flow separation attack angle. Moreover, increasing the jet momentum coefficient can enhance the flow control effect. The findings of this study could provide guidance for the flow control application of air-supplement PSJs.

show abstract

Section: Flow Field Comparison Under Different Actuation States At Di...supporting

confidence: 79%

mentioning

confidence: 99%

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

et al. 2022

View full text Add to dashboard Cite

show abstract

“…Separation control at moderate-Reynolds number ONERA; Xiamen University; UNINA [35,72,73] Jet noise control ONERA [12,74,75] Shock wave/boundary layer interaction control UT Austin; AFEU; NUDT [18,[76][77][78][79][80][81][82][83] In separation control cases, PSJs are typically issued upstream of the separation region, either in the wall-normal direction to create a quasi-streamwise counter-rotating vortex pair [84] or pitched and skewed with respect to the main flow to produce a single dominant streamwise vortex [12]. These vortices transport the high-momentum flow from the outer boundary layer to the near-wall region, resulting in a fuller boundary layer velocity profile and a reduction in boundary layer shape factor (1.3-1.2 in [84]).…”

Section: Institutions Representative Literaturesmentioning

confidence: 99%

“…At a freestream velocity of 40 m/s (chord-based Reynolds number: Re c = 1.2 × 10 6 ) and an angle of attack of 11.5 • , the separation region initially occupying half of the chord shrinks monotonically when the actuation frequency increases, and a fully attached flow is obtained at f d > 250 Hz. In [73], three PSJAs are employed to control the flow separation over an NACA 0021 wing model at U ∞ = 20 m/s and Re c = 3.4 × 10 5 . Different actuation locations (0.15c and 0.45c) and jet pitching angles (45 • and 60 • ) are examined.…”

Section: Institutions Representative Literaturesmentioning

confidence: 99%

Plasma Synthetic Jet Actuators for Active Flow Control

et al. 2018

View full text Add to dashboard Cite

The plasma synthetic jet actuator (PSJA), also named as sparkjet actuator, is a special type of zero-net mass flux actuator, driven thermodynamically by pulsed arc/spark discharge. Compared to widely investigated mechanical synthetic jet actuators driven by vibrating diaphragms or oscillating pistons, PSJAs exhibit the unique capability of producing high-velocity (>300 m/s) pulsed jets at high frequency (>5 kHz), thus tailored for high-Reynolds-number high-speed flow control in aerospace engineering. This paper reviews the development of PSJA in the last 15 years, covering the major achievements in the actuator working physics (i.e., characterization in quiescent air) as well as flow control applications (i.e., interaction with external crossflow). Based on the extensive non-dimensional laws obtained in characterization studies, it becomes feasible to design an actuator under several performance constraints, based on first-principles. The peak jet velocity produced by this type of actuator scales approximately with the cubic root of the non-dimensional energy deposition, and the scaling factor is determined by the electro-mechanical efficiency of the actuator (O(0.1%–1%)). To boost the electro-mechanical efficiency, the energy losses in the gas heating phase and thermodynamic cycle process should be minimized by careful design of the discharge circuitry as well as the actuator geometry. Moreover, the limit working frequency of the actuator is set by the Helmholtz natural resonance frequency of the actuator cavity, which can be tuned by the cavity volume, exit orifice area and exit nozzle length. In contrast to the fruitful characterization studies, the application studies of PSJAs have progressed relatively slower, not only due to the inherent difficulties of performing advanced numerical simulations/measurements in high-Reynolds-number high-speed flow, but also related to the complexity of designing a reliable discharge circuit that can feed multiple actuators at high repetition rate. Notwithstanding these limitations, results from existing investigations are already sufficient to demonstrate the authority of plasma synthetic jets in shock wave boundary layer interaction control, jet noise mitigation and airfoil trailing-edge flow separation.

show abstract

“…26 Generated by the instantaneous energy deposition from a high voltage pulsed arc discharge, 27 the pressure within the actuator chamber can reach a value of hundreds of kilopascals. 28 Since PSJA has abundant advantages such as no need for moving parts and external air sources, 25 high jet velocity, [29][30][31] wide-bandwidth, 32 and extremely fast response, 33,34 its application prospects in the flow control field are becoming more and more promising. 35 Owning the merits of both simple structure and high instantaneous pressure rise, PSJA might be suitable to be an ice breaker.…”

Section: Introductionmentioning

confidence: 99%

A novel de-icing strategy combining electric-heating with plasma synthetic jet actuator

Gao

Luo

Zhou

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Traditional electro-thermal de-icing strategy has the drawback of high energy consumption and its heat knife accounts for a considerable amount of the cost. Compared to electro-thermal de-icing, thermo-mechanical expulsion de-icing system eliminates the heat knife by combining electric-heating with electro-magnetic expulsion de-icing system. The consumption is significantly lower but the system has complex mechanical structures. In this article, a novel de-icing strategy combining electric-heating with plasma synthetic jet actuator is proposed for the first time. Its main idea is to replace heat knife with a simple mechanical device. During the de-icing process, the electric-heating is used to remove the adhesion force, then a single pulse of plasma synthetic jet actuator exerts a rapid force on ice and makes it fracture. Schlieren imaging shows plasma synthetic jet actuator can make free ice columns fracture into pieces and powder. The ice can even be completely penetrated by pressurized air when the discharge energy is relatively large. And compared with the non-deicing process, the intensities of waves and jets are significantly weakened. During the hybrid de-icing process, high-speed photography shows that plasma synthetic jet actuator can divide an ice layer 200 mm in diameter and 10 mm in thickness into multiple blocks completely in tens of milliseconds after electric-heating removes the adhesion force. Besides, energy consumption of plasma synthetic jet actuator in a de-icing cycle accounts for only 0.27% of the whole system. Compared with the free ice columns of the same size, the ice debonded by electric-heating fragmented into smaller blocks after activating plasma synthetic jet actuator. However, heating for too long does not bring more beneficial effects on the fracture of ice in this experiment. At last, a new “micro piston ice-breaker” which is waterproof is proposed to meet the needs of in-flight de-icing.

show abstract

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Cited by 24 publications

References 28 publications

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

Plasma Synthetic Jet Actuators for Active Flow Control

A novel de-icing strategy combining electric-heating with plasma synthetic jet actuator

Contact Info

Product

Resources

About