Airfoil Leading and Trailing Edge Separation Control Using SDBD Plasma Actuators
نویسنده
چکیده
Wind tunnel experiments were conducted to understand boundary layer separation control on airfoils. The objective of this research was to better implement flow control strategies with single dielectric barrier discharge (SDBD) plasma actuator designs for airfoils that exhibit both leading and trailing edge stall characteristics at realistic flight speeds and Reynolds numbers. The NASA energy efficient transport (EET) airfoil was a platform to study the effect of plasma actuators on leading edge stall and boundary layer separation in a strong adverse pressure gradient, while the V-22 Osprey airfoil was used to study trailing edge stall with separation in a weaker adverse pressure gradient.
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