Tip Vortex Control via an Active Trailing-Edge Tab
Author:
Affiliation:
1. McGill University, Montreal, Quebec H3A 2K6, Canada
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.18202
Reference20 articles.
1. Concepts for reduction of blade/vortex interaction noise
2. Experimental observations of two-dimensional blade-vortex interaction
3. Airfoil pressure measurements during a blade vortex interaction and a comparison with theory
4. Head-on parallel blade-vortex interaction
5. Analysis of a higher harmonic control test to reduce blade vortex interaction noise
Cited by 4 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献
1. Onset of orbital motion in a trailing vortex from an oscillating wing;Journal of Fluid Mechanics;2018-10-02
2. The structure of a trailing vortex from a perturbed wing;Journal of Fluid Mechanics;2017-07-10
3. Aeroelastic response and limit cycle oscillations for wing-flap-tab section with freeplay in tab;Journal of Fluids and Structures;2017-01
4. Effectiveness of Dynamically Deflected Tab Control of a Tip Vortex;AIAA Journal;2007-12
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