Experimental Investigation of the Influence of a Reverse Delta Type Add-on Device on the Flap-tip Vortex of a Wing

[摘要] Particle Image Velocimetry was used in a low speed wind tunnel to investigate the effect of interactions of vortices produced by an outboard flap-tip of a half wing (NACA 23012 in landing configuration) and a slender reverse delta type add-on device, placed in the proximity of the outboard flap-tip, on the upper surface of the half wing. This work investigates the characteristics of the vortex interactions generated downstream in planes perpendicular to the free stream direction at a chord-based Reynolds number of Rec=2.74×105. It was found that the add-on device significantly reduces the tangential velocity magnitude and enlarges the vortex core of the resultant vortex by up to 36.1% and 36.8%, respectively.

[发布机构] School of Engineering and Computer Sciences, New York Institute of Technology, P.O. Box 5464, Abu Dhabi, United Arab Emirates^1;Mechanical Engineering Department, University of Tripoli, P.O. Box 81507, Tripoli, Libya^2;Mechanical Engineering Department, International Islamic University Malaysia, P.O. Box 10, Kuala Lumpur; 50728, Malaysia^3

[效力级别] 无线电电子学 [学科分类] 航空航天科学

[关键词] Chord-based Reynolds number;Experimental investigations;Landing configurations;Low-speed wind tunnel;Particle image velocimetries;Tangential velocities;Upper surface;Vortex interactions