LES of Separated-flow Controlled by DBD Plasma Actuator around NACA 0015 over Reynolds Number Range of 10^4-10^6
Author:
Affiliation:
1. Japan Aerospace Exploration Agency (JAXA)
2. Ryoyu Systems Company, Ltd.
3. University of Tokyo
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2015-0308
Reference48 articles.
1. Dielectric Barrier Discharge Plasma Actuators for Flow Control
2. Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators
3. Separation Control Using Plasma Actuators: Dynamic Stall Vortex Control on Oscillating Airfoil
4. SDBD plasma enhanced aerodynamics: concepts, optimization and applications
5. Large Eddy Simulation of Plasma-Based Control Strategies for Bluff Body Flow
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1. Computational Study of the Plasma Actuator Flow Control for an Airfoil at Pre-Stall Angles of Attack;Applied Sciences;2022-09-09
2. Separation Control by Plasma Actuators: Effects of Direct Momentum Injection and Vortex Generation;Flow, Turbulence and Combustion;2019-11-30
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