Analysis of nonlinear aeroelastic response of curved panels under shock impingements

Abstract

This study focuses on the fluid–structure interaction of two-dimensional flexible curved panels subjected to an impinging oblique shockwave in inviscid supersonic flow. A fluid–structural coupling solver is employed to simulate the nonlinear aeroelastic responses of four curved panels under different incident shock strengths. The responses, comprising the static deformation, flutter onset, and post-flutter are determined and compared to those of flat panel and shock-free conditions. The curvature effects, shock–shock interaction, as well as incident strengths, have profound influences on the solution. In the absence of incident shock condition, the greater the curvature of the panel, the smaller the critical flutter dynamic pressure. In the condition of shock impingement, for the smaller curvature, strong incident shock can advance the flutter onset, and there exist multiple solutions under different initial conditions; while for the larger curvature, strong incident shock can suppress the flutter onset, and the travel-like oscillation is observed at post-flutter.