Quasi-two-dimensional method for the computation of the dual-mode scramjet flow path was developed by introducing one-dimensional method for completed combustion to the two-dimensional N-S equation. The influences to the scramjet performance by shock and boundary layer separation were handled by this method.In addition,the thrust and impulse as well as the parameter variations along the axis direction of the scramjet were given in acceptable time. Validated by the computation of a freejet scramjet engine, the effects of different positions of fuel injection and flowpath on the engine performance were analyzed.