Plasma-Based Control of Shock-Wave / Boundary-Layer Interaction
Author:
Affiliation:
1. U.S. Air Force Research Laboratory
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2006-1007
Reference35 articles.
1. Sliding Discharge Application in Aerodynamics
2. Separation Control on High Angle of Attack Airfoil Using Plasma Actuators
3. Flow Re-attachment and Acceleration by Paraelectric and Peristaltic Electrohydrodynamic (EHD) Effects
Cited by 7 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Control of High-Angle-of-Attack Reentry Flow with Plasma Actuators;Journal of Spacecraft and Rockets;2013-03
2. Numerical Investigation of Oblique Shock-Wave/Turbulent Boundary-Layer Interaction Control Using Plasma Actuators;41st AIAA Fluid Dynamics Conference and Exhibit;2011-06-14
3. Numerical Investigation of Shock-wave/Boundary-Layer Interaction Control Using Plasma Actuators;49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition;2011-01-04
4. Numerical Simulation of Direct Current Glow Discharges for High-Speed Flow Control;Journal of Propulsion and Power;2008-09
5. Control of Shock-Wave / Boundary-Layer Interaction Using Volumetric Energy Deposition;46th AIAA Aerospace Sciences Meeting and Exhibit;2008-01-07
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