Experimental control of swept-wing transition through base-flow modification by plasma actuators

Journal article (2018)

Authors

Srikar Yadala Aerodynamics - Aerospace Engineering , Université de Poitiers
M.T. Hehner Aerodynamics - Aerospace Engineering , University of Stuttgart
J. Serpieri Aerodynamics - Aerospace Engineering
Nicolas Benard CNRS-Université de Poitiers-ISAE-ENSMA
Philipp C. Dörr University of Stuttgart
Markus J. Kloker University of Stuttgart
M. Kotsonis Aerodynamics - Aerospace Engineering
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
Copyright: © 2018 Srikar Yadala, M.T. Hehner, J. Serpieri, Nicolas Benard, Philipp C. Dörr, Markus J. Kloker, M. Kotsonis
DOI: https://doi.org/10.1017/jfm.2018.268
Boundary layer control Boundary layer stability Instability control
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Published Date

13-04-2018

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

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.