Experimental control of swept-wing transition through base-flow modification by plasma actuators
Srikar Yadala Venkata (Université de Poitiers, TU Delft - Aerodynamics)
M.T. Hehner (TU Delft - Aerodynamics, University of Stuttgart)
J. Serpieri (TU Delft - Aerodynamics)
Nicolas Benard (CNRS-Université de Poitiers-ISAE-ENSMA)
Philipp C. Dörr (University of Stuttgart)
Markus J. Kloker (University of Stuttgart)
M. Kotsonis (TU Delft - Aerodynamics)
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Abstract
Control of laminar-to-turbulent transition on a swept-wing is achieved by base-flow modification in an experimental framework, up to a chord Reynolds number of 2.5 million. This technique is based on the control strategy used in the numerical simulation by Dörr & Kloker (J. Phys. D: Appl. Phys., vol. 48, 2015b, 285205). A spanwise uniform body force is introduced using dielectric barrier discharge plasma actuators, to either force against or along the local cross-flow component of the boundary layer. The effect of forcing on the stability of the boundary layer is analysed using a simplified model proposed by Serpieri et al. (J. Fluid Mech., vol. 833, 2017, pp. 164–205). A minimal thickness plasma actuator is fabricated using spray-on techniques and positioned near the leading edge of the swept-wing, while infrared thermography is used to detect and quantify transition location. Results from both the simplified model and experiment indicate that forcing along the local cross-flow component promotes transition while forcing against successfully delays transition. This is the first experimental demonstration of swept-wing transition delay via base-flow modification using plasma actuators.