TY - JOUR
T1 - Experimental control of swept-wing transition through base-flow modification by plasma actuators
AU - Yadala Venkata, S.
AU - Hehner, Marc T.
AU - Serpieri, Jacopo
AU - Benard, Nicolas
AU - Dörr, Philipp C.
AU - Kloker, Markus J.
AU - Kotsonis, Marios
PY - 2018/4/13
Y1 - 2018/4/13
N2 - 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.
AB - 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.
KW - boundary layer control
KW - boundary layer stability
KW - instability control
UR - http://www.scopus.com/inward/record.url?scp=85045318846&partnerID=8YFLogxK
UR - http://resolver.tudelft.nl/uuid:813e16e4-9a17-4ffe-b5b9-58c9837604ec
U2 - 10.1017/jfm.2018.268
DO - 10.1017/jfm.2018.268
M3 - Article
SN - 0022-1120
VL - 844
JO - Journal of Fluid Mechanics
JF - Journal of Fluid Mechanics
ER -