图书馆订阅: Guest
Begell Digital Portal Begell 数字图书馆 电子图书 期刊 参考文献及会议录 研究收集
流动显示和图像处理期刊
SJR: 0.161 SNIP: 0.312 CiteScore™: 0.1

ISSN 打印: 1065-3090
ISSN 在线: 1940-4336

流动显示和图像处理期刊

DOI: 10.1615/JFlowVisImageProc.v13.i3.40
pages 265-286

EXPERIMENTAL INVESTIGATIONS ON FLUIDIC CONTROL OVER AN AIRFOIL

S. Bourgois
Laboratoire d'Etudes Aérodynamiques, Ecole Nationale Supérieure de Mécanique et d'Aérotechnique, Téléport 2, 1 Avenue Clement Ader B. P. 40109, 86961 Futuroscope Chasseneuil CEDEX, France
Jean Tensi
Laboratoire d'Etudes Aérodynamiques, Ecole Nationale Supérieure de Mécanique et d'Aérotechnique, Téléport 2, 1 Avenue Clement Ader B. P. 40109, 86961 Futuroscope Chasseneuil CEDEX, France
E. Sommier
Laboratoire d'Etudes Aérodynamiques, Ecole Nationale Supérieure de Mécanique et d'Aérotechnique, Téléport 2, 1 Avenue Clement Ader B. P. 40109, 86961 Futuroscope Chasseneuil CEDEX, France
J. Favier
Institut de Mécanique des Fluides de Toulouse, Allee du Professeur Camille Soula, 31400 Toulouse, France

ABSTRACT

This study presents the development of two fluidic actuators − namely, microjets and tangential blowing actuator (TBA), designed for flow separation control. The developed actuators are compact enough to fit inside an ONERA D profiled wing with a chord of 0.35 m. Test bench experiments showed that the microjets (resp. TBA) were able to produce exit velocities up to 330 m/s (resp. 60 m/s). These actuators were placed in the model and were tested in wind tunnels for various blowing rates. The investigations included the use of force balance measurements, on-surface flow visualization with pigmented oil, off-surface flow visualizations with smoke, surface pressure distribution measurements, and Particle Image Velocimetry (PIV). Most of the tests were performed at free-stream velocities between 20 m/s (for PIV) and 40 m/s, corresponding to Reynolds numbers in the range 0.47 × 106−0.93 × 106 . The angle of attack varied from −2 to 20 degrees. Experiments were conducted using the naturally occurring laminar boundary layer as well as for a turbulent boundary layer. In such a case, rough strips were used in the vicinity of the leading edge. The present tests show the efficiency of these devices to delay separation and improve aerodynamic performances of the wing: for example, a maximum of 30% gain in CL has been reached using the microjets. Both actuators tend to increase the lift coefficient CL after stall and areas of separated flow have been eliminated by applying control, as suggested by flow visualizations and PIV velocity fields.


Articles with similar content:

EXPERIMENTAL STUDY OF TANGENTIAL BLOWING EFFECT OF SUPERSONIC JET ON AERODYNAMICS OF A SUPERCRITICAL WING AT TRANSONIC SPEEDS
TsAGI Science Journal, Vol.42, 2011, issue 4
Petr Vladimirovich Savin, Vsevolod Davydivich Bokser, Albert Vasilievich Petrov
POSSIBILITY OF PASSIVE CONTROL OF A SWEPT FLAT PLATE BOUNDARY LAYER
TSFP DIGITAL LIBRARY ONLINE, Vol.2, 2001, issue
Shibani Bose, Yasuaki P. Kohama, Mitsuru Shimagaki
LIFT ENHANCEMENT OF AN AIRFOIL USING LEADING EDGE TRIANGULAR PROTUBERANCES FOR SMALL SCALE WIND TURBINE BLADES
Proceedings of the 24th National and 2nd International ISHMT-ASTFE Heat and Mass Transfer Conference (IHMTC-2017), Vol.0, 2017, issue
Raghavendra S, Sathyabhama A, Jayapal Reddy C
Large Eddy Simulation of Supersonic Jet Plumes from Rectangular Con-Di Nozzles
ICHMT DIGITAL LIBRARY ONLINE, Vol.0, 2012, issue
P. C. Wang, James J. McGuirk
Heat Transfer Downstream of Laminar, Transitional and Turbulent Flow Separations
Heat Transfer Research, Vol.29, 1998, issue 6-8
L. E. Yushina, Eleonora Ya. Epik, Tatyana T. Suprun