Abstract: Based on the flow pattern stniccure obtained from free flight experiments, a method of solving the low supersonic, high Revnolds numbers separated flow problem is proposed in this paper by which the inviscid region of the afterbody flowfield of a sphere has been simulated numerically. Flow characteristics, such as separated shock, wake shock, separation line and wake structure, obtained from computation are in good agreement with the experimental results. The detailed flow structure in the after body flowfi...