Wind Tunnel Investigation on Dynamic behavior of 80°/65° Double Delta Wing in Rolling at High Incidence
80°/65°双三角翼摇滚特性风洞实验研究

Free rolling test technique including apparatus, methods as well as data acquisition in a high-speed wind tunnel is presented in this paper. The test was carried out in a FL-23 wind tunnel with Mach number ranging from 0.3 to 0.6 and Reynolds number ranging from 0.56×10 7/m to 1.126×10 7/m. An investigation on the dynamic behavior of a double delta wing at high incidence was conducted. Dynamic motions were obtained on a double delta wing that was free to rotate on its longitudinal axis at different attack angle. Different dynamic rolling motions including steady stability, quasi-limit-cycle rock motion, and double period's oscillations were observed. Results show that the rocking of double delta wing is restrained as the Mach number increasing, the wing rocking motion is also influenced by attack angle, initial state has no influence on ultimate balance state and rolling amplitude of double delta wing.