No AccessHelicopter Lift Force Increase in Hover Mode by NS-SDBD Plasma ActuatorsAndrey Starikovskiy and Richard B. MilesAndrey StarikovskiyPrinceton UniversitySearch for more papers by this author and Richard B. MilesPrinceton UniversitySearch for more papers by this authorAIAA 2018-0936Session: Plasma Actuators IIPublished Online:7 Jan 2018https://doi.org/10.2514/6.2018-0936SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookXLinked InRedditEmail About Previous chapter Next chapter FiguresReferencesRelatedDetailsSee PDF for referencesCited byNoise Reduction on a Model Helicopter Rotor Using Dielectric Barrier Discharge Plasma ActuatorsDor Polonsky, Oksana Stalnov and David Greenblatt 31 March 2023 | AIAA Journal, Vol. 61, No. 7Battery-Powered Helicopter Hover Performance Enhancement using DBD Plasma ActuatorDor Polonsky, Stalnov Oksana and David Greenblatt8 June 2023Rotor performance enhancement by alternating current dielectric barrier discharge plasma actuation31 October 2022 | Plasma Science and Technology, Vol. 25, No. 1Large eddy simulation of dynamic stall flow control for wind turbine airfoil using plasma actuator1 Dec 2020 | Energy, Vol. 212 What's Popular 2018 AIAA Aerospace Sciences Meeting 8–12 January 2018Kissimmee, Floridahttps://doi.org/10.2514/6.2018-0936 CrossmarkInformationCopyright © 2018 by Andrey Starikovskiy, Nikita Persikov, Richard Miles. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. TopicsActuatorsAerodynamic PerformanceAerodynamicsAeronauticsAerospace SciencesAvionicsBoundary LayersFluid DynamicsVortex Dynamics KeywordsFree Stream VelocityHelicopter RotorPlasma ActuatorAngle of AttackAerospace EngineeringFlow VelocityEnergy DistributionRetreating Blade StallEnergy ConsumptionElectrical SystemsDigital Topics Plasmadynamics and Lasers