Computational Analysis of Swept Wing Dynamic Response to Step Increases in Angle of Attack

View Video Presentation: https://doi.org/10.2514/6.2023-4002.vid The unsteady aerodynamic performance of a swept wing is modeled using Ansys Fluent for a dynamic pitch and hold simulation. The time responses of flow structures and wing loadings are investigated using transient URANS simulations in which the wing angle of attack is maintained constant, increased at a constant pitching rate, and then held constant at a new angle of attack 5° greater than the initial angle. The pitch rate is high (ω+ = 0.07) such that the simulations model 5° step increases in angle of attack, as might be encountered with a sudden updraft gust. The NACA 643-618 wing has a leading-edge sweep of 30° and a taper ratio of one. The inflow is steady with a Mach number of 0.05 and Reynolds number of 10^5. Significant differences in flow structures and dynamic response were observed between cases where the wing was pitched beyond its angle of leading-edge stall and those where it was not. The massively separated leading edge stall dynamics were found to be highly dependent on interactions with the wingtip vortex.