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Design of a Delta Wing Aircraft
2017 International Conference on Mechatronics, Electronics and Automotive Engineering (ICMEAE), 2017This work shows a UAV (Unmanned Aerial Vehicle) modeling of a fixed wing type and a delta wing configuration. The selection of an aerodynamic profile and the aircraft dimension was chosen. On a CAD package the geometric design was created, where the finite element analysis and fluid dynamics shows that the behavior of the aircraft follows the ...
Luis Raul Montano Perez +2 more
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Study of the Reverse Delta Wing
Journal of Aircraft, 2011Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures of a slender reverse delta wing at various angles of attack and roll. This work investigates the characteristics of the vortices generated downstream in planes perpendicular to the freestream direction and their dependence on angles of attack and roll ...
Afaq Altaf +3 more
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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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44th AIAA Aerospace Sciences Meeting and Exhibit, 2006
The paper discusses the topology of the skin -friction line pattern on a 65 -deg swept delta wing with special attenti on to the flow on the apex that usually is poorly resolved in experiments. A large -scale model of the apex was constructed to obtain a better insight into the flow.
Niek Verhaagen, Barbara Van Bossuyt
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The paper discusses the topology of the skin -friction line pattern on a 65 -deg swept delta wing with special attenti on to the flow on the apex that usually is poorly resolved in experiments. A large -scale model of the apex was constructed to obtain a better insight into the flow.
Niek Verhaagen, Barbara Van Bossuyt
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2006
A well-known category of flows where Boussinesq’s hypothesis is expected to fail is vortex-dominated flows. Unfortunately, many of the flows of industrial interest involve vortices, such as those emanating from the roof of a car, or from the wing tips of airplanes. The delta wing is another example of a flow where the accurate resolution of the physics
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A well-known category of flows where Boussinesq’s hypothesis is expected to fail is vortex-dominated flows. Unfortunately, many of the flows of industrial interest involve vortices, such as those emanating from the roof of a car, or from the wing tips of airplanes. The delta wing is another example of a flow where the accurate resolution of the physics
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The delta wing in oscillatory gusts
AIAA Journal, 1980This report describes systematic aerodynamic lift and pitching moment measurements on two sharp edged delta wings of aspect ratio 1 and 2 in oscillatory vertical gusts of varying frequency parameter and gust amplitude. The effects of the nonlinearity associated with the separated flow region are explored and the influence of the potential flow and the ...
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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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Flow Visualization of Wing Vortices of Delta Wings
Journal of Fluids Engineering, 2023Philipp Epple +2 more
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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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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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