Abstract: Since 1982, Ni, Davis et al.have developed a time-dependent finite volume method combined with multiple-grid technique. It is an explicit scheme by which a steady state solution can be obtained rapidly. This paper adopts the method to compute the transonic flow field through plane cascades. First, elementary ideas and treatment principles of Ni-Davis scheme are clarified. The numerical treatments on solid wall boundary are then improved. The artificial viscous terms used are stated. With numerical tests, an improved algorithm for multiple-grid technique is presented. Finally, two examples of transonic flow fields through plane cascades are described. The computational accuracy and efficiency of numerical results are acceptable for aerodynamic design of aero-engine. Computing a steady state solution on a 65×17 grid takes about 15 minutes CPU time on IBM 4341 computer. With multiple-grid scheme, the savings in CPU time is about 50% to 60%.

Key words: finite volume method, multiple-grid technique, numerical treatments on boundary