Experimental Investigation of Asymmetric Vortex Breakdown Flow Control by Microperturbation over Highly Swept Wings-Reference-Cited by-同舟云学术

Experimental Investigation of Asymmetric Vortex Breakdown Flow Control by Microperturbation over Highly Swept Wings

Published:2018-11 Issue:6 Volume:31 Page:04018101
ISSN:0893-1321
Container-title:Journal of Aerospace Engineering
language:en
Short-container-title:J. Aerosp. Eng.

Author:

Wu Guangxing¹

Affiliation:

1. Assistant Researcher, Institute of Engineering Thermophysics and Key Laboratory of Wind Energy Utilization, Chinese Academy of Sciences, 11 Beisihuanxi Rd., Beijing 100190, China; Assistant Researcher, National Laboratory of Wind Turbine Blade Research and Development Center, 11 Beisihuanxi Rd., Beijing 100190, China.

Publisher

American Society of Civil Engineers (ASCE)

Subject

Mechanical Engineering,Aerospace Engineering,General Materials Science,Civil and Structural Engineering

Link

http://ascelibrary.org/doi/pdf/10.1061/%28ASCE%29AS.1943-5525.0000922

Reference21 articles.

1. Numerical investigation of vortex breakdown on a delta wing

2. Arena A. and R. Nelson. 1989. “The effect of asymmetric vortex wake characteristics on a slender delta wing undergoing wing rock motion.” In Proc. 6th Atmospheric Flight Mechanics Conf. 3348. Reston VA: AIAA.

3. A combined experimental and analytical investigation of the vortex stability over sharp-edged slender bodies

4. Influence of nose perturbations on behaviors of asymmetric vortices over slender body

5. Testing technique of PIV in low-speed wind tunnel;Chen Y.;J. Exp. Fluid Mech.,2007

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