2000 年 48 巻 560 号 p. 490-494
This is a review paper of unsteady aerodynamics of a 45°delta wing in rolling motion, based on experimental data collected from the wind tunnel testing at Nagoya University. This wing shows self-induced oscillations at high angles of attack, which seem to be different from those of conventional slender wing rock. The flow physics of this oscillation can be made clear from results of free-to-roll testing for various values of pitch angle. Furthermore, the static rolling moment shows highly nonlinear characteristics with regard to roll angle, which is associated with asymmetric behavior of a pair of leading-edge vortices. Due to this nonlinear change of rolling motion, there occurs a hysteresis of rolling moment.