Unsteady aerodynamics of free-to-roll nonslender delta wings
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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.
|Item Type||Conference or Workshop Items (Paper)|
|Creators||McClain, A., Wang, Z., Vaidaki, E. and Gursul, I.|
|Uncontrolled Keywords||flow separation,motion compensation,angle of attack,wings|
|Departments||Faculty of Engineering & Design > Mechanical Engineering|
|Research Centres||Aerospace Engineering Research Centre|
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