Numerical Study Of Airfoil RAE2822 And ONERA M6 Three-Dimensional Wing

In this thesis,the multiple working conditions,large scale and high accuracy numerical simulation of high Reynolds number airfoil RAE2822 and ONERA M6 three-dimensional wing are carried out by using the implicit large eddy simulation method,and the simulation results are compared and analyzed in detail.The main contents are as follows:(1)The implicit large eddy simulation is performed for the RAE28822 supercritical air-foil with Mach number 0.729,Reynolds number 6.5×10~6and angle of attack of 2.31~°.The numerical simulation results are verified by the mesh convergence test of the pressure coeffi-cient and friction resistance coefficient and the comparison of the pressure coefficient/friction resistance coefficient with the experimental results.And the shock wave-turbulent boundary layer interaction on the upper surface of the airfoil is studied.The statistical characteristics of the turbulence and the visualization of the coherent structures in the vicinity of the shock wave are analyzed.The root-mean-square of the velocity fluctuation,Reynolds stress,turbu-lent kinetic energy production,dissipation and distribution mechanisms are mainly analyzed during the disturbance process.The results show that the occurrence of shock waves has a significant effect on the amplitude and peak position of the velocity fluctuation and Reynold-s stress,and a large amount of turbulent kinetic energy generates during the disturbance process,and the main dissipative region of turbulent kinetic energy is still near the wall.The distribution mechanism is not a generation-dissipation balance but a complex balance.(2)The implicit large eddy simulation is performed for the ONERA M6 airfoil with Mach number 0.8395,Reynolds number 1.172×10~7and angle of attack of 3.06~°.The cal-culation results clearly show that theshock at the tail end and the rich turbulent structure in the boundary layer.And before about 40%of the chord length,the boundary layer is com-posed of large-scale vortex structures,and a large number of horseshoe vortices can be seen,which develop downstream along the flow direction.These vortices gradually rise and are stretched,and then broken and formed into a large number of small-scale structures and en-tering into a turbulent state.This process has the typical mechanism of turbulence generation and the typical evolution characteristics of TS waves.This study has certain reference value for the design of large aircraft wing in China.At the same time,the implicit large eddy simulation method can obtain a lot of turbulent pul-sation information,and can capture many unstable states which the RANS method can not do.The large-scale effect and quasi-sequential vortex structure in the non-equilibrium pro-cess can contribute to the study of the flow mechanism and guide the improvement of the RANS method.