Computation of the aeroelastic response of a flexible delta wing at high angles of attack

To perform relevant aeroelastic analyses for a delta wing at an angle of attack, a computational technique capable of addressing both complex nonlinear aerodynamics and nonlinear structural features is presented. This numerical method couples a well-validated Euler/Navier–Stokes code (Euler computations only in present work) with a nonlinear finite-element plate model. The resulting aeroelastic solver is used to simulate a 60° sweep flexible delta wing for angles of attack from 5° to 40°. When vortex breakdown is present over the wing, increased buffeting of the wing is observed consistent with previous experimental observations. Comparisons of the computed r.m.s. wingtip acceleration with experimentally measured values shows good qualitative agreement. Spectral analysis of the wingtip deflection and acceleration show the first structural mode to be the dominant mode with participation also from the second and third mode.