Investigation of two aeroelasticity problems in transonic flow

Transonic control surface buzz and wing flutter influence the flight performance and safety seriously. In order to investigate the problem deeply, the unstructured dynamic mesh technique is introduced to simulate the movement of the rudder and flutter response of the AGARD445.6 wing. Full implicit dual-time temporal derivatives and cell-center finite volume method spatial derivatives are adopted to solve the Euler equations and treat the unsteady aerodynamic problem. The structural equations of motion for their simultaneous time integration with the governing flow equations are marched by Rung-Kutta in the time domain. Considering the influence of a gap and an upper-wing spoiler, transonic control surface buzz is intensively studied. The phenomenon of the upper-wing spoiler suppressing the buzz is presented and the mechanism of the upper-wing spoiler suppressing the buzz is researched. The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter dip with the bottom near the domain which Mach number is 1. Comparisons between computing and experimental flutter characteristics show good agreement, giving confidence in the accuracy of the aeroelastic capability that was developed.