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Vortex Dynamics of Delta Wings
1989The typical angle of attack for maximum lift of a delta wing is about 35°, which is much higher than for a two-dimensional airfoil. The delta wing is, therefore, suitable for highly maneuverable aircraft. In this paper, experimental results for delta wings is reviewed. The review is made from the perspective of fundamental fluid dynamic mechanisms.
Mario Lee, Chih-Ming Ho
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Fluid Dynamics, 1994
On the basis of experimental wind tunnel research, a topological classification of possible delta wing flow regimes is given and a diagram in angle of attack-sweep angle coordinates is constructed. A regime with two pairs of symmetrically disposed whirlwind like vortices formed on the surface of the wing is detected.
Betyaev, S. K., Brysov, O. P.
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On the basis of experimental wind tunnel research, a topological classification of possible delta wing flow regimes is given and a diagram in angle of attack-sweep angle coordinates is constructed. A regime with two pairs of symmetrically disposed whirlwind like vortices formed on the surface of the wing is detected.
Betyaev, S. K., Brysov, O. P.
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Turbulence in the Wake of a Delta Wing
1996Although the aerodynamics of delta wings has been studied extensively, remarkably little attention has been devoted to the downstream wake. In the present work we study the large- and small-scale turbulent structure in the trailing vortex wake, with a view to understanding the basic instabilities, vertical mixing and decay rate of the primary vortex ...
G. D. Miller, C. H. K. Williamson
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Applied Mechanics Reviews, 1990
On a delta wing, the separation vorticies can be stationary due to the balance of the vorticity surface flux and the axial convection along the swept leading edge. These stationary vortices keep the wing from losing lift. A highly swept delta wing reaches the maximum lift at an angle of attack of about 40°, which is more than twice as high as that of a
Mario Lee, Chih-Ming Ho
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On a delta wing, the separation vorticies can be stationary due to the balance of the vorticity surface flux and the axial convection along the swept leading edge. These stationary vortices keep the wing from losing lift. A highly swept delta wing reaches the maximum lift at an angle of attack of about 40°, which is more than twice as high as that of a
Mario Lee, Chih-Ming Ho
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Euler solutions for delta wings
AIAA Journal, 1990Nomenclature b =wing semispan c = speed of sound M — Mach number Mc — Mach number of velocity component normal to ray from wing apex Ms = Mach number of velocity component normal to upstream side of shock p = pressure S5 = (shock spanwise location)/Z?
Andrew B. Wardlaw, Stephen F. Davis
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Flow Visualization of Wing Vortices of Delta Wings
Journal of Fluids Engineering, 2023Philipp Epple +2 more
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Self-induced wing rock of slender delta wings
7th Atmospheric Flight Mechanics Conference, 1981As part of a research program aimed at exploring basic mechanisms that cause wing rock in combat aircraft, an investigation was conducted to study the aerodynamic factors which cause the low-speed wing rock exhibited by slender delta wings. A flat-plate delta wing with 80 deg leading-edge sweep was subjected to conventional static-force tests and ...
L. NGUYEN, L. YIP, J. CHAMBERS
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Control of wing-rock motion of slender delta wings
Journal of Guidance, Control, and Dynamics, 1993A theoretical analysis is conducted to determine the optimal control input for wing-rock suppression through a Hamiltonian formulation. The optimality equations are analyzed through Beecham-Titchener's averaging technique and numerically integrated by a backward-differentiation formulas method developed for implicit differential equations.
Jia Luo, C. Edward Lan
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DSMC Calculations for The Delta Wing
1991In this study, a general three-dimensional direct simulation Monte Carlo (DSMC) program (developed by G. A. Bird) is used. The molecular collisions are modeled using the variable hard sphere (YHS) molecular model which treats the molecules as hard spheres as far as the scattering angle distribution is concerned, but the collision cross section depends ...
M. Cevdet Celenligil, James N. Moss
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Similitude relations for buffet and wing rock on delta wings
Progress in Aerospace Sciences, 1997Abstract Vortex flow phenomena at high angles of incidence are of great interest to the designers of advanced combat aircraft. The steady phenomena (such as steady lift and pitching moments) are understood fairly well, whereas the unsteady phenomena are still uncertain. This paper addresses two important unsteady phenomena on delta wings. With regard
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