Non-uniform recovery of vortex breakdown over delta wing in response to blowing along vortex core
Author:
Publisher
Springer Science and Business Media LLC
Subject
Fluid Flow and Transfer Processes,General Physics and Astronomy,Mechanics of Materials,Computational Mechanics
Link
http://link.springer.com/content/pdf/10.1007/BF01893304.pdf
Reference18 articles.
1. Atta R; Rockwell D (1990) Leading-edge vortices due to low reynolds number flow past a pitching delta wing. AIAA J 28(6): 995–1004
2. Bradley RG; Whitten PD; Wray WO (1976) Leading-edge vortex augmentation in compressible flow. J Aircraft 13(9): 238–242
3. Campbell JF (1976) Augmentation of vortex lift by spanwise blowing. J Aircraft 13(9): 727–732
4. Gad-el-Hak M; Ho CM (1986) Unsteady vortical flow around three dimensional lifting surface. AIAA J 24(5): 713–721
5. Gu W; Robinson O; Rockwell D (1993) Control of vortices on delta wing by leading-edge injection. AIAA 31(7): 1177–1186
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1. Semi-span wind tunnel testing without conventional peniche;Experiments in Fluids;2017-11-08
2. Forebody Slot Blowing on Vortex Breakdown and Load Over a Delta Wing;AIAA Journal;2008-03
3. Effects of Forebody Slot Blowing on Vortex Breakdown and Load over a Delta Wing;45th AIAA Aerospace Sciences Meeting and Exhibit;2007-01-08
4. Control of Vortex Breakdown over a Delta Wing Using Forebody Spanwise Slot Blowing;AIAA Journal;2007-01
5. Unsteady Vortex Structure over Delta-Wing Subject to Transient Along-Core Blowing;AIAA Journal;1998-09
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