Results 261 to 270 of about 151,552 (312)
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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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Vortex breakdown over a pitching delta wing
32nd Aerospace Sciences Meeting and Exhibit, 1994Unsteady pressure measurements were carried out on a pitching delta wing in order to study the effects of pressure gradient on the phase lag between the wing motion and the movement of breakdown location. The results indicate that the observed time lag of breakdown location is strongly linked to the external pressure gradient generated by the wing.
I. Gursul, H. Yang
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Nonlinear Supersonic Potential Flow over Delta Wings
AIAA Journal, 1981A numerical procedure has been developed for the computation of the steady, inviscid supersonic flow over aircraft configurations. The technique accounts for major nonlinear effects (shock waves, blunt leading edges) at low to moderate supersonic speeds.
Grossman, B., Siclari, M. J.
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Reactive Flow Control of Delta Wing Vortex
AIAA Guidance, Navigation, and Control Conference and Exhibit, 2006In this paper, the reactive flow control of delta-wing leading-edge vortices using along-core pulse-widthmodulation flow injection is presented. Leading-edge vortices on the upper surface of a delta wing can augment lift. Manipulating breakdown points of leading-edge vortices can effectively change the delta wing’s lift and drag and generate attitude ...
Yong Liu +6 more
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Direct Measurement of Delta-Wing Vortex Circulation
AIAA Journal, 1998The circulation around a closed path encompassing the primary vortex of stationary delta wings has been investigated through the use of a novel ultrasound technique. Ultrasonic pulses propagating in clockwise and counterclockwise directions enclosed a fixed path that was positioned perpendicular to the delta-wing root chord line.
H. Johari, J. Moreira
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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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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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Flow visualization study of delta wings in wing-rock motion
7th Applied Aerodynamics Conference, 1989Water tunnel flow visualizations have been conducted for the wing-rock phenomenon in the cases of models having different leading-edge sweeps and roundness. Wing rock, which is noted to occur in the absence of asymmetric vortex liftoff, vortex breakdown, and static hysteresis, is seen to be initiated by flowfield asymmetries that are induced by flow ...
T. NG, GERALD MALCOLM, LIANE LEWIS
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Flow Visualization of Wing Vortices of Delta Wings
Journal of Fluids Engineering, 2023Philipp Epple +2 more
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Wing rock of double delta wings
AIAA Atmospheric Flight Mechanics Conference and Exhibit, 2001Saimon Otaka +2 more
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