Effect of an electrostatic field on boundary- layer transition.

Ketcham, J.; Velkoff, Henry R.

doi:10.2514/3.4756

Cited by 49 publications

(14 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Alterations in the boundary layer thickness were also observed by Jukes and Choi The plasma actuator orientation used above is capable of maintaining an attached flow past the angle of natural separation on both a flat plate, [19], and an airfoil [20]. shows that the flow successfully re-attaches to the surface of the airfoil.…”

Section: Orientation and Placement Of Dbd Plasma Actuatorsupporting

confidence: 54%

Sounding Rocket Roll Control Through DBD Plasma Actuated Boundary Layer Control

Sumanik

Etele

2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

View full text Add to dashboard Cite

Dielectric Barrier Discharge (DBD) plasma actuators induce a plasma flow that alters the velocity of the surrounding air across a surface. The induced flow, directed tangential to the surface, inputs momentum to the boundary layer. This analysis examines the feasibility of a simplified boundary condition within computational fluid dynamic (CFD) simulations of a DBD plasma actuator mounted on a rocket fin. The simulations examine the location of the plasma actuator through a range of freestream velocities. Resulting in a plasma actuator location between 40% and 45% of the fin chord producing the most force. With the actuator at 50% chord a velocity range between 10 and 90 m/s is tested. The highest normal force experienced by the fin due to plasma actuation is approximately 5.5 mN/m at a freestream 70 m/s decreasing as the rocket decelerates. This force and the resulting torque induces an angular velocity of 2.86 RPM of roll on a sounding rocket. iii List of Tables vii List of Figures viii List of Acronyms x List of Symbols xi List of Tables

show abstract

Section: Orientation and Placement Of Dbd Plasma Actuatorsupporting

confidence: 54%

Sounding Rocket Roll Control Through DBD Plasma Actuated Boundary Layer Control

Sumanik

Etele

2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

View full text Add to dashboard Cite

show abstract

“…Plasma actuators were initially developed by Velkoff and Ketchman [199] in the late 1960s, while their application as flow-control devices was first investigated in the 1990s [200][201][202]. Over the years, numerous investigations concerning flow-separation control and aerodynamic enhancement using plasma actuation surfaced [203][204][205][206][207][208][209][210][211][212][213][214][215][216][217][218].…”

Section: Plasma Actuatorsmentioning

confidence: 99%

Review of Flow-Control Devices for Wind-Turbine Performance Enhancement

Akhter

Omar

2021

Energies

View full text Add to dashboard Cite

It is projected that, in the following years, the wind‐energy industry will maintain its rapid growth over the last few decades. Such growth in the industry has been accompanied by the desirability and demand for larger wind turbines aimed at harnessing more power. However, the fact that massive turbine blades inherently experience increased fatigue and ultimate loads is no secret, which compromise their structural lifecycle. Accordingly, this demands higher overhaul‐and‐maintenance (O&M) costs, leading to higher cost of energy (COE). Introduction of flow‐control devices on the wind turbine is a plausible solution to this issue. Flow‐control mechanisms feature the ability to effectively enhance/suppress turbulence, advance/delay flow transition, and prevent/promote separation, leading to enhancement in aerodynamic and aeroacoustics performance, load alleviation and fluctuation suppression, and eventually wind turbine power augmentation. These flow‐control devices are operated primarily under two schemes: passive and active control. Development and optimization of flow‐control devices present the potential for reduction in the COE, which is a major challenge against traditional power sources. This review performs a comprehensive and up‐to‐date literature survey of selected flow‐control devices, from their time of development up to the present. It contains a discussion on the current prospects and challenges faced by these devices, along with a comparative analysis centered on their aerodynamic controllability. General considerations and conclusive remarks are presented after the discussion.

show abstract

“…A near-surface plasma layer can be created in various ways. For example, in [198,199] and later publications [200,201], DC discharges with electrodes located above or on the airfoil surface were used. In this case, the ionic wind generated in the discharge can Zone size when actuator is off Fig.…”

Section: Flow Separation Control Using Ionic Windmentioning

confidence: 99%

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

Starikovskiy

Aleksandrov

2021

Plasma Phys. Rep.

View full text Add to dashboard Cite

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.

show abstract

Effect of an electrostatic field on boundary- layer transition.

Cited by 49 publications

References 2 publications

Sounding Rocket Roll Control Through DBD Plasma Actuated Boundary Layer Control

Sounding Rocket Roll Control Through DBD Plasma Actuated Boundary Layer Control

Review of Flow-Control Devices for Wind-Turbine Performance Enhancement

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

Contact Info

Product

Resources

About