Unsteady aerodynamics of free-to-roll nonslender delta wings

A McClain, Z Wang, E Vaidaki, I Gursul

Research output: Contribution to conferencePaper

6 Citations (Scopus)

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.
Original languageEnglish
Pages12961-12974
Number of pages14
Publication statusPublished - 2007
Event45th AIAA Aerospace Sciences Meeting and Exhibit - Reno, Nevada
Duration: 1 Jan 2007 → …

Conference

Conference45th AIAA Aerospace Sciences Meeting and Exhibit
CityReno, Nevada
Period1/01/07 → …

Keywords

  • Flow separation
  • Motion compensation
  • Angle of attack
  • Wings

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    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, .