It focuses on an approach to generating 2D unstructured grids for the solution of Euler equations.Unlike the generation of unstructured grids before with background grids,the background information needed in Avancing Front Method is obtained directly with the distance to the airfoil surface.In solving the Euler equations,the cell centered finite volume method is used for space discretization,and four step Runge Kutta method is adopted for time marching.Two kinds of boundary condition are presented and three kinds of boundary conditions are applied and analyzed.The calculated results are given and discussed.

A numerical method is presented for calculating the unsteady transonic viscous flows around oscillating aerofoil and wing based on the unsteady Navier-stokes equations.It adopts an implicit NND algorithm and Baldwin-Lomax turbulence model in solving procedure.The computational grid is C and C-H types in a body-fitted coordinate system generated by an algebraical method. The transonic viscous flows around the NACA 0012 aerofoil and M6 wing with pitching oscillation have been calculated.Numerical results are in good agrement with experimental data.

The aeroelastic behaviour of wings with different types of separated vortex at high incidences is investigated.The unsteady aerodynamic equations and the equations of motion are solved simultaneously in the time domain.The separated vortices shed-ding from the leading-edge and/or side-edge of wings are taken into account by an improved Nonlinear Vortex-Lattice Method.The equations of motion are integrated by Runge-Kutta Method.Wings with different planforms at different basic incidences are consid-ered.It is found that (1) the separated vortex shedding from the leading-or side-edges results in the critical flutter speed of the wing lower,and the higher the basic incidence,the lower the critical flutter speed.(2) the smaller the sweep of wing,the smaller the in-fluence of separated vortex on the aeroelastic characteristics.(3) at certain flight speeds and basic incidences,stable limit cycles ap-pear,and the amplitudes of limit cycles even keep constant when the initial distu rbances of response vary.