Abstract:

Through transformations, the time-dependent boundary conditions on the airfoil contour and the boundary conditions at infinity are brought fixed to the boundaries of a finite domain. The boundary conditions can thus be satisfied exactly without increasing the computational time. The novel scheme is useful for computing transonic, strong disturbance, unsteady folws with high reduced frequencies. The scheme makes use of curvefitted orthogonal meshes and the lettice-control technique to obtain the optimal grid distribution. The numerical results are satisfactory.

Key words: numerical computation, transonic flow, unsteady flow, conformsl transformation