Transonic Wing Flutter Simulation Using Navier-Stokes and k-ω Turbulent Model

** † ‡ § § In this paper, a new three-dimensional time-accurate Navier-Stokes aeroelastic solver is developed with the k-ω turbulent model. The developed program adopts various numerical schemes to guarantee the accuracy and stability of the aeroelastic solution. A dual-time stepping method based on the diagonalized-ADI algorithm is applied to improve the time accuracy. A second-order staggered algorithm is also employed to reduce the lagging errors between the fluid and structural solvers. The use of parallel processing based on the multigrid system reduces wall-clock time. Aeroelastic computations of the wing are carried out for transonic and low supersonic Mach numbers. In each case the k-ω turbulent model is implemented to account for turbulent effects. The computed flutter points are compared with other computed results and the wind tunnel test. In this research, flutter analysis based on the Baldwin-Lomax turbulent model is also performed to investigate the influence of the turbulent model. The comparison result shows that the computed flutter boundaries using Wilcox's k-ω model is more comparable to the experimental data.