Aeroelastic Simulation of High-Aspect Ratio Wings with Intermittent Leading-Edge Separation

We present a medium-fidelity aeroelastic framework for computing intermittently separating three-dimensional (3-D) flows around high-aspect ratio wings with significantly reduced computational cost compared to the computational-fluid- dynamics-based method. To achieve that, we propose modified vortex panel method leading-edge separation controlled by suction parameter theory, and its incorporation in coupled solver dynamic response of these systems. Numerical verifications simulations are presented on both attached separated test cases, demonstrating postflutter limit-cycle oscillation cantilever wing, deploying complex kinematic response. In cases were able capture interactions flowfields using low cost.