Aerodynamic stability testing of compressors requires the use of distortion generators to simulate the inlet total pressure distortion flow field. Traditional design of such generators involves a repetitive process of trial-and-error, testing, and modification, which leads to long design cycles and difficulties in ensuring accuracy. This paper, based on the principle of boundary vorticity, investigates the design technology for simulating plate-type total pressure distortion generators. The influence of geometric features such as the width, height, and edge shape of the simulating plate on the downstream flow field structure and distortion parameters is analyzed. An intrinsic relationship between the simulating plate contour and the vorticity distribution is discovered, and the mechanism by which vortex pairs cause the expansion of the low-pressure region is revealed. Based on this mechanism, a design method is developed to inversely design the shape of the simulating plate according to the vorticity distribution to control the low-pressure region's configuration. The area of the low-pressure region is then precisely controlled by adjusting the geometrically similar contours of the plate. This method achieves the desired profile of the simulating plate in just two iterations, providing an effective technique for high-efficiency and high-precision distortion simulation in compressor aerodynamic stability tests.