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Numerical simulation of incidence and sweep effects on delta wing vortex breakdownThe structure of the vortical flowfield over delta wings at high angles of attack was investigated. Three-dimensional Navier-Stokes numerical simulations were carried out to predict the complex leeward-side flowfield characteristics, including leading-edge separation, secondary separation, and vortex breakdown. Flows over a 75- and a 63-deg sweep delta wing with sharp leading edges were investigated and compared with available experimental data. The effect of variation of circumferential grid resolution grid resolution in the vicinity of the wing leading edge on the accuracy of the solutions was addressed. Furthermore, the effect of turbulence modeling on the solutions was investigated. The effects of variation of angle of attack on the computed vortical flow structure for the 75-deg sweep delta wing were examined. At moderate angles of attack no vortex breakdown was observed. When a critical angle of attack was reached, bubble-type vortex breakdown was found. With further increase in angle of attack, a change from bubble-type breakdown to spiral-type vortex breakdown was predicted by the numerical solution. The effects of variation of sweep angle and freestream Mach number were addressed with the solutions on a 63-deg sweep delta wing.
Document ID
19950037635
Document Type
Reprint (Version printed in journal)
Authors
Ekaterinaris, J. A.
Schiff, Lewis B.
Date Acquired
August 16, 2013
Publication Date
September 1, 1994
Publication Information
Publication: Journal of Aircraft
Volume: 31
Issue: 5
ISSN: 0021-8669
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Other