Aerodynamic improvement of a delta wing in combination with leading edge flaps
نویسندگان
چکیده
منابع مشابه
The leading-edge vortex of swift wing-shaped delta wings
Recent investigations on the aerodynamics of natural fliers have illuminated the significance of the leading-edge vortex (LEV) for lift generation in a variety of flight conditions. A well-documented example of an LEV is that generated by aircraft with highly swept, delta-shaped wings. While the wing aerodynamics of a manoeuvring aircraft, a bird gliding and a bird in flapping flight vary signi...
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Instead of using conventional flaps to generate torques, we explore the feasibility of applying micromachined sensors and actuators to control leading-edge vortices, and consequently, provide sufficient moments for flight control. By utilizing a “flexible skin” containing 64 micromachined shear stress sensors, instantaneous separation line on the leading edges can be detected. We applied microa...
متن کاملEffect of Angle of attack on Stability Derivatives of a Delta wing in Hypersonic Flow with Straight leading edge
In the present paper effect of angle of attack on stability derivatives in pitch of delta wing for the attached shock case is been studied. A strip theory is used in which strips at different span-wise locations are independent. This combines with the similitude to give a piston theory. In the present theory, the similitude, and the piston theory have been extended to a flat wing with straight ...
متن کاملEffect of Angle of Attack on Stability Derivatives of a Delta Wing with Straight Leading Edge in Supersonic Flow
In the Present paper effect of angle of incidence on pitching derivatives of a delta wing with Straight leading edges for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent. This combines with similitude to give a piston theory. From the results it is seen that with the increase in the Mach number, ther...
متن کاملOscillating Supersonic delta wing with Straight Leading Edges
A Supersonic similitude has been used to obtain stability derivatives in pitch and roll of a delta wing with straight leading edge for the attached shock case. Ghosh’s strip theory is been used in which strips at different span wise locations are independent of each other. This combines with the similitude to give a piston theory which gives the closed form of solution to stability derivatives ...
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ژورنال
عنوان ژورنال: Theoretical and Applied Mechanics Letters
سال: 2017
ISSN: 2095-0349
DOI: 10.1016/j.taml.2017.11.010