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.
|Number of pages||14|
|Publication status||Published - 2007|
|Event||45th AIAA Aerospace Sciences Meeting and Exhibit - Reno, Nevada|
Duration: 1 Jan 2007 → …
|Conference||45th AIAA Aerospace Sciences Meeting and Exhibit|
|Period||1/01/07 → …|
- Flow separation
- Motion compensation
- Angle of attack
McClain, A., Wang, Z., Vaidaki, E., & Gursul, I. (2007). Unsteady aerodynamics of free-to-roll nonslender delta wings. 12961-12974. Paper presented at 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, .