Research Information System
44th AIAA Aerospace Sciences Meeting 2006, Reno, NV, United States Of America, 9 - 12 January 2006, vol.17, pp.12791-12806, (Full Text)
In the research effort, the drooping leading edge concept has been investigated computationally. The current study is an extension of the work carried out by W. Geissler and M. Trenker in a generalized way for a cambered airfoil, and is focused on finding the effect of different parameters based on which the control strategy can be further refined/optimized. The parameters in focus are the percentage of drooping leading edge (4), the amplitude of drooping leading edge angle (θ) and the frequency of drooping leading edge (k d) with respect to airfoil oscillating frequency (ka). The analysis was concentrated towards the higher angle-of-attack region. The mean angle of attack was 15° and the maximum amplitude of oscillation was 10°. This covered the range of oscillating airfoil from 5° to 25°. The 25° angle is well beyond the stall angle (steady state) of a cambered airfoil without any high lift devices. The results obtained are very promising and have resulted in better control of reducing the strength of dynamic stall vortex.