The Mesh Processing Of The Wing Trailing Edge Effect On Aerodynamic

With the level of computer hardware continuously improving, Computational Fluid Dynamics has been using in engineering practice widely and deeply. Scale and complexity of CFD, efficiency, precision and so on are also put forward higher requirements. The precision of CFD depends on the quality of grid mostly. Therefore, the grid generation technology becomes an important part of the Computational Fluid Dynamics. The general airfoil and blade aerodynamic characteristics are more sensitive to the processing method of the trailing edge grid. So the airfoil trailing edge grid processing is a key technology of CFD. In view of this, this article selects different airfoil and blade to discuss the mesh processing of the wing trailing edge effect on aerodynamic. At first the work calculated the original airfoil GA(W)-1(one-element), GA(W)-1(two-element), S809, NASA SC(2)0614, PHASE VI blades and DLR- F6(WBNP) by applying Fluent commercial software, and then by changing the grid of the airfoil, blade and wing trailing edge to study its effect on aerodynamic characteristics. Finally, according to the calculation results and experimental data, the research gives the optimal scheme.For the blunt trailing edge aerodynamic shape, the numerical simulation results show that trailing edge without any treatment and have a viscous trail mesh are closed to the experimental values. But it costs a lot of grids and calculates more. If the trailing edge is sharped, in the low speed conditions, the trailing edge point is located in the point that above 1/3 thickness of trailing edges original under surface. In the high speed conditions, the trailing edge point is located in the point that at the trailing edges original under surface. The result is more accuracy and can reduce the number of gird. In addition to some extent, it improves the computational efficiency.