6. Physics of a Fluid, Neutral and Ionized Gases

CONTROL OF FLOW SEPARATION ON A WING USING ELECTRICAL DISCHARGE

Andrey A. Sidorenko
1. Khristianovich Institute of Theoretical and Applied Mechanics SB RAS Novosibirsk, Russian Federation
2. Novosibirsk State University Novosibirsk, Russian Federation
Boris Yu. Zanin
1. Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences Novosibirsk, Russian Federation
2. Novosibirsk State University Novosibirsk, Russian Federation
zanin@itam.nsc.ru
Boris V. Postnikov
1. Khristianovich Institute of Theoretical and Applied Mechanics SB RAS Novosibirsk, Russian Federation
The material was received by the Editorial Board: 29.07.2011
Separation control experiments on a rectangular wing were carried out using dielectric barrier discharge plasma at subsonic speed for chord Reynolds numbers between 0,35 and 1·106 . Surface pressure measurements and flow visualization show that global flow separation on the wing can be mitigated or eliminated with the plasma actuators. The data were obtained for a wide range of angle of attack, flow speed, plasma excitation frequency and power. Various means of discharge influence on separated flow were investigated, including acoustic one.

Keywords:
subsonic flow, flow separation, rectangular wing, control of separated flow, electrical discharge. 
УДК 532.526.5

CONTROL OF FLOW SEPARATION ON A WING USING ELECTRICAL DISCHARGE
References: Sidorenko A. A., Zanin B. Yu., Postnikov B. V., Budovskiy A. D. CONTROL OF FLOW SEPARATION ON A WING USING ELECTRICAL DISCHARGE. Vestnik NSU. Series: Physics. 2012, vol. 7, no. 1. P. 15–27 (in Russ.). DOI: 10.54362/1818-7919-2012-7-1-15-27