Numerical Simulations Of The Wake Vortex Of The Civil Aviation Aircraft

With the continuous development of aviation industry, existing wake safety interval has already placed restrictions on the growth of air traffic flow. As the result, the wingtip vortex which is the most important part of the wake should be intensive studied, in order to provide a reference for the theoretical analysis of the wake interval narrowing.In the modern time, numerical simulation has been a most economic and efficient method of solving the questions of hydrodynamics, therefore, at first, using different eddy viscosity models including S-A model, Realizable k-? model and k-? SST model to carry out the numerical simulation of the flow around the two-dimensional NACA0012 airfoil with different angles of attack as well as different Mach number and the process of the rolling up of the wingtip vortex around the three-dimensional NACA0012 wing based on ANSYS, then compared with experimental data of wind tunnel to assess the advantages and disadvantages of these eddy viscosity models and research the characteristic of the wingtip vortex. At last, to simulate the formation and dissipation of wingtip vortex of the civil aviation aircraft with and without wingtip vortex diffuser based on Realizable k-? model,for the sake of the application of the wingtip vortex diffuser.Compared with the static pressure coefficient, lift coefficient curve, polar curve, axial component of vorticity, eddy viscosity, streamline and pictures of flow field, we find that Realizable k-? model gains a better accurate prediction of the simulation and wingtip vortex diffuser can not only improve aircraft performance but also reduce eddy energy and the scale of the wake vortex by making a division on the wingtip vortex.