Characterization of plasma synthetic jet actuator with Laval-shaped exit and application to drag reduction in supersonic flow
Author:
Affiliation:
1. National University of Defense Technology, Changsha 410073, China
2. China Aerodynamics Research and Development Center, Mianyang 621006, China
Funder
National Natural Science Foundation of China
Natural Science Foundation of Hunan Province
National Science and Technology Major Project
Publisher
AIP Publishing
Subject
Condensed Matter Physics,Fluid Flow and Transfer Processes,Mechanics of Materials,Computational Mechanics,Mechanical Engineering
Link
https://aip.scitation.org/doi/pdf/10.1063/5.0064533
Reference49 articles.
1. Recent developments in DBD plasma flow control
2. SYNTHETIC JETS
3. Direct numerical simulation of drag reduction by spanwise oscillating dielectric barrier discharge plasma force
4. Effect of dielectric barrier discharge plasma actuator on the dynamic moment behavior of pitching airfoil at low Reynolds number
5. Characterization of Three-Electrode SparkJet Actuator for Hypersonic Flow Control
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