Abstract: As a continuation of the work, this paper deals with unsteady aerodynamic forces on the wing-body-tail complex form and interferences among the various components. For the sake of simplification, the shock is assumed to be weak and the angle of attack small, thus the problem is linearized. The method of moving vortex finite elementary solution is used to solve the initial boundary value problem of wave equation. Elementary solution comes from refe-rence. The mesh is similar to that adopted in reference, but care must be taken to conform the mesh of wing to that of the tail so as to prevent the wake vortex of wing from coming too near to the control point of tail lest the calculation should be unstable. The calculation starts from the time t = 0. It is necessary to solve a system of algebraic equations for circulation at each time. Numerical calculations are performed for various blast orientations and elevation angles and different complex plane forms. The variations of lift and moment coefficients with the time are given in figures 2 to 6, which show that due to the increase of meshes for complex plane form the convergence of results is Not so good as that for the wing. Downwash effect of wing on tail is also given. The obtained results of lift coefficients for wing-body quite agree with the experimental data.