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Unsteady aerodynamics of free-to-roll nonslender delta wings


Reference:

McClain, A., Wang, Z., Vaidaki, E. and Gursul, I., 2007. Unsteady aerodynamics of free-to-roll nonslender delta wings. In: 45th AIAA Aerospace Sciences Meeting and Exhibit, 2007-01-01, Reno, Nevada.

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Abstract

An experimental investigation on free-to-roll delta wings with A=50° has been conducted. Roll time histories showed that multiple trim positions are possible. Only nonzero roll angles, or a combination of zero and nonzero roll angles, are possible, depending on the angle of attack. It was found that the free-to-roll dynamics is closely correlated with the static lift characteristics at zero roll angle. In a small range of incidences, self-excited roll oscillations are observed. The effects of leading-edge shape and wing thickness on the self-excited roll oscillations were investigated. The self-excited roll oscillations are also observed for the wing with sharp leading-edge (for which the separation point is fixed), but are much smaller in amplitude. As the amplitude of the motion is amplified for a round leading-edge, characteristics of flow separation at the leading-edge are a contributing factor. It is suggested that the interaction of the reattachment lines play an important role in the self-excited roll oscillations.

Details

Item Type Conference or Workshop Items (Paper)
CreatorsMcClain, A., Wang, Z., Vaidaki, E. and Gursul, I.
Uncontrolled Keywordsflow separation, motion compensation, angle of attack, wings
DepartmentsFaculty of Engineering & Design > Mechanical Engineering
Research CentresAerospace Engineering Research Centre
RefereedNo
StatusPublished
ID Code1558

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