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

3rd International Conference on Mechanical, Automotive and Aerospace Engineering 2016

机械制造;无线电电子学;航空航天工程

Altaf, A.^1 ; Thong, T.B.^1 ; Omar, A.A.^2 ; Asrar, W.^3

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

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

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/184/1/012002/pdf
DOI  :  10.1088/1757-899X/184/1/012002

学科分类：航空航天科学

来源: IOP

【 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.