Quick Search Adv Search
   Home  About Journal  Editorial Board  Instruction  Subscription  Download  Message  Contact
JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A 2001, Vol. 27 Issue (6) :658-661    DOI:
论文 Current Issue | Next Issue | Archive | Adv Search << Previous Articles | Next Articles >>
Drag Reduction Technique of Cylinder and Mechanism Research
TAN Guang-kun1, WANG Jin-jun1, LI Qiu-sheng2*
1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics;
2. City University of Hong Kong, Dept. of Building and Construction

Abstract
Reference
Related Articles
Download: PDF (0KB)   HTML 1KB   Export: BibTeX or EndNote (RIS)      Supporting Info
Abstract The hydrogen bubble flow visualization technique has been used to study the flow around a hollow circular cylinder with several splits and the drag reduction mechanism. The experiments cover the cylinder with different number and arrangement of splits, different angle of attack. The primary criterion of drag reduces is whether the splits change wake of the hollow cylinder. According to this criterion, the experimental result indicates when the attack of a split is in the range of |α|≤60°, the cylinder possesses drag reduction characteristics, and the optimum angle of attack is 20°. Under this condition, a two-dimensional jet flow is visible in the downstream split, which affects the wake flow pattern. However, when the attack of the split is equal to 70°≤|α|≤90°, the split can hardly affect the drag of the cylinder.
Service
Email this article
Add to my bookshelf
Add to citation manager
Email Alert
RSS
Articles by authors
Keywordsdrag reduction   cylinders   separated flow   flow visualization     
Received 2000-04-26;
About author:
Cite this article:   
TAN Guang-kun, WANG Jin-jun, LI Qiu-sheng.Drag Reduction Technique of Cylinder and Mechanism Research[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2001,V27(6): 658-661
URL:  
http://bhxb.buaa.edu.cn//EN/     or     http://bhxb.buaa.edu.cn//EN/Y2001/V27/I6/658
Copyright 2010 by JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A