2011 Third International Conference on Measuring Technology and Mechatronics Automation 2011
DOI: 10.1109/icmtma.2011.314
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Experimental Investigation of Airfoil Suction Side Flow Separation Control by Spanwise Nanosecond Actuation

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Cited by 4 publications
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“…The wake-physics analysis of this actuator revealed similar phenomena, indicating a series of quasi-planar and spherical compression waves, followed by spanwise vortices in the post-stall regime [224]. Moreover, the flow controllability of a nanosecond discharge plasma actuator (NDPA) [225] could be described with impressive aerodynamic enhancements of stall delay (6 • ), lift augmentation (30%), and drag reduction (22%), which make it superior over micro discharge actuators, as signified by the supremacy of the remarkable shock-effect over the momentum-effect. Additionally, NDPA is effective for dynamic-stall control [226], with steady lift and moment growth accompanying flow reattachment at high Strouhal number (St e > 2) excitation.…”
Section: Plasma Actuatorsmentioning
confidence: 91%
“…The wake-physics analysis of this actuator revealed similar phenomena, indicating a series of quasi-planar and spherical compression waves, followed by spanwise vortices in the post-stall regime [224]. Moreover, the flow controllability of a nanosecond discharge plasma actuator (NDPA) [225] could be described with impressive aerodynamic enhancements of stall delay (6 • ), lift augmentation (30%), and drag reduction (22%), which make it superior over micro discharge actuators, as signified by the supremacy of the remarkable shock-effect over the momentum-effect. Additionally, NDPA is effective for dynamic-stall control [226], with steady lift and moment growth accompanying flow reattachment at high Strouhal number (St e > 2) excitation.…”
Section: Plasma Actuatorsmentioning
confidence: 91%