받음각이 있는 3차원 날개의 주파수/시간 영역 천음속 플러터 해석

Abstract

In this study, a nonlinear aeroelastic analysis for a wing-box structure model has been conducted in the transonic and supersonic flow region. The transonic small disturbance code was incorporated into the analysis system to consider aerodynamic nonlinear effects. In frequency domain, the transient pulse method (TPM) and P-k method was used and in time domain, the fully coupled time-integration method (CTIM) was applied. The static aeroelastic computation has been conducted to obtain the converged deformed wing shape and initial aerodynamic loadings. Both the vibration characteristics and the nonlinear aeroelastic responses of the present wing model are presented for several angle-of attack conditions. Also, the computed flutter boundaries are presented and compared in the frequency and time domains.