Flow Separation Control over a NACA 0015 Airfoil Using Nanosecond-Pulsed Plasma Actuator

Zheng, Jianguo; Cui, Yongdong; Zhao, Zijie; Li, Jiun-Ming; Khoo, Boo Cheong

doi:10.2514/1.j056111

Cited by 19 publications

(15 citation statements)

References 29 publications

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“…The present work reports hydrodynamic force measurements and flow visualizations with particle image velocimetry (PIV) around a circular arc plate in nominally 2D flow to relate the forces to the associated flow patterns. Indeed, as highlighted, for example, in [21], the joint analysis of forces and flowfield proves very helpful to get a better insight into the physics of the flow and may be useful in the perspective of flow control [22]. The tested section, the experimental setup, and data processing are presented in Sec.…”

mentioning

confidence: 99%

Force Variations Related to Flow Pattern Changes Around a High-Camber Thin Wing

Bot

2020

AIAA Journal

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confidence: 99%

Force Variations Related to Flow Pattern Changes Around a High-Camber Thin Wing

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2020

AIAA Journal

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“…57). In this case, at positive angles of attack, the stagnation point of the flow shifts to the lower surface of the airfoil and turns out to be further upstream than the zone of maximum discharge energy deposition, which is located near the leading edge of In contrast to [213,231], in [232,233] the actuator was used in the standard geometry: the exposed electrode was located upstream and the encapsulated electrode was located downstream. The trailing edge of the exposed electrode, from which the discharge started, was not on the airfoil axis, but shifted from the leading edge by 0.5% of the chord.…”

Section: Effect Of Actuator Position On Efficiency Of Flow Controlmentioning

confidence: 99%

“…The trailing edge of the exposed electrode, from which the discharge started, was not on the airfoil axis, but shifted from the leading edge by 0.5% of the chord. Since, in [232,233], the NACA-0015 airfoil was also used at practically the same Reynolds numbers (Re = 3.06 × 10 5 for [231] and Re = 2.68 × 10 5 for [233]), it becomes possible to directly compare the efficiency of these two geometries of ns-SDBD actuators. Shown in Fig.…”

Section: Effect Of Actuator Position On Efficiency Of Flow Controlmentioning

confidence: 99%

Gasdynamic Flow Control by Ultrafast Local Heating in a Strongly Nonequilibrium Pulsed Plasma

Starikovskiy

Aleksandrov

2021

Plasma Phys. Rep.

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Abstract— The paper presents a review of modern works on gasdynamic flow control using a highly nonequilibrium pulsed plasma. The main attention is paid to the effects based on ultrafast (on the nanosecond time scale for atmospheric pressure) local gas heating, since, at present, the main successes in controlling high-speed flows by means of gas discharges are associated with this thermal mechanism. Attention is paid to the physical mechanisms responsible for the interaction of the discharge with gas flows. The first part of the review outlines the most popular approaches for pulsed energy deposition in plasma aerodynamics: nanosecond surface barrier discharges, pulsed spark discharges, and femto- and nanosecond optical discharges. The mechanisms of ultrafast heating of air at high electric fields realized in these discharges, as well as during the decay of the discharge plasma, are analyzed separately. The second part of the review gives numerous examples of plasma-assisted control of gasdynamic flows. It considers control of the configuration of shock waves in front of a supersonic object, control of its trajectory, control of quasi-stationary separated flows and layers, control of a laminar–turbulent transition, and control of static and dynamic separation of the boundary layer at high angles of attack, as well as issues of the operation of plasma actuators in different weather conditions and the use of plasma for the de-icing of a flying object.

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“…Potocar et al [17] investigated the flow around a NACA4421 turbine blade at Re number of 7,600 and 10,500. Zheng et al [21] placed a symmetrical plasma actuators on SC(2)-0714 supercritical airfoil model to show the effect of the plasma actuators for controlling the turbulent boundary layer separation at high Re numbers. They reported that input energy influences the plasma actuator effectiveness in flow control around the turbine blade.…”

Section: Introductionmentioning

confidence: 99%

“…They reported that input energy influences the plasma actuator effectiveness in flow control around the turbine blade. [23] Zheng et al [21] reported that increase in actuation frequency is suppressed the flow separation and delayed it downstream. In a numerical study of Khoshkoo and Jahangirian, [19] the effect of the unsteady plasma body force is compared with that of steady force over a stalled NACA0015 airfoil at Re = 4.5 × 10 4 .…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic and energy‐efficiency‐based assessment of plasma actuator's position on a NACA0015 airfoil

Akbıyık

Yavuz

Akansu

2019

Contributions to Plasma Physics

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In recent years, there has been an increase in the number of research papers on plasma and its use in active flow control applications. The main objective of this study is to assess the plasma actuator's position on a NACA0015 airfoil in terms of aerodynamic forces. In addition, optimization of the plasma actuator's position and its configuration are studied in order to identify the optimum configuration for improvement in lift coefficient. The experiments are conducted in an open-suction-type wind tunnel at Reynolds numbers of 48,000, 75,000, and 100,000. The plasma actuators are mounted on various positions (x/C) starting from the leading edge to trailing edge of the airfoil. The experimental results on aerodynamic force measurement are presented to illustrate the increasing lift effect of the generated plasma. It is also shown that the plasma actuators used as an active flow control device appears to shift the stall angle of the airfoil. The results of the experimental study suggest that the energy efficiency of airborne systems can be improved with the use of plasma actuators due to its increasing lift coefficient effect. This result becomes a vital finding considering that the same flight can be achieved with less fuel and less amount of environmental pollution for the same distance of journey. It is also worth mentioning that increasing lift effect would mean taking off from a shorter runway or allowing the airborne vehicle with the ability to fly with additional payload. K E Y W O R D Sairfoil, energy efficiency, lift coefficient, plasma actuator, stall angle

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Flow Separation Control over a NACA 0015 Airfoil Using Nanosecond-Pulsed Plasma Actuator

Cited by 19 publications

References 29 publications

Force Variations Related to Flow Pattern Changes Around a High-Camber Thin Wing

Force Variations Related to Flow Pattern Changes Around a High-Camber Thin Wing

Gasdynamic Flow Control by Ultrafast Local Heating in a Strongly Nonequilibrium Pulsed Plasma

Aerodynamic and energy‐efficiency‐based assessment of plasma actuator's position on a NACA0015 airfoil

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