DocumentCode
2740511
Title
The oscillation delta wing at the high angle of attack
Author
Shumsky, Gennady
Author_Institution
Novosibirsk State Tech. Univ., Russia
Volume
3
fYear
2004
fDate
26 June-3 July 2004
Firstpage
75
Abstract
A mathematical model was constructed and was used to study the oscillation slender delta wing at the angles of attack. The wing´s unsteady aerodynamic characteristics were determined on the basis of nonlinear theory of wing. The flow separation at the high angles of attack can appear. The numerical studies were conducted with application of two typical wing flow field regimes (including high angles of attack).
Keywords
aerodynamics; aircraft; flow instability; flow separation; fluid oscillations; attack angle; flow separation; mathematical model; oscillation slender delta wing; unsteady aerodynamic characteristics; wing flow field regimes; Aerodynamics; Ash; Cyclones; Dispersion; Electric breakdown; Gases; Laboratories; Powders; Publishing; Purification;
fLanguage
English
Publisher
ieee
Conference_Titel
Science and Technology, 2004. KORUS 2004. Proceedings. The 8th Russian-Korean International Symposium on
Print_ISBN
0-7803-8383-4
Type
conf
DOI
10.1109/KORUS.2004.1555678
Filename
1555678
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