Design method for plane blade grid shock wave control of transonic compressor

The invention provides a design method for plane blade grid shock wave control of a transonic compressor. The method comprises the following steps: carrying out numerical simulation analysis on an original transonic compressor plane blade grid to determine the incident position of the original strong shock wave on the suction surface of the blade such that a bump model formula is acquired; providing a mounting range of the bump on a blade, further obtaining different parameter combinations of the bump, substituting the different parameter combinations into the bump model formula to form different bumps, and determining the bump with the optimal parameter combination by comparing a shock wave system structure and a drag reduction effect of a bump blade grid with the different parameter combinations; acquiring a new suction surface by using the obtained bulge molded surface data of the optimal parameter combination in combination with a programming tool, and then forming a new planar blade grid by the suction s