China is carrying out the research and development of bleed air anti-icing system of a large civil aircraft wing, and the design of the system with independent intellectual property rights has not yet been put into operation. In this paper, based on the design principle of bleed air anti-icing system of an aircraft wing, according to the flow distribution calculation method of the piccolo, the SIMULINK model of the pipeline simulation was established, and the pressure, temperature, flow distribution in the pipe of the piccolo under different working conditions were analyzed. Subsequently, this paper established a set of test bench system for ground flow distribution, and obtained the pressure drop and temperature drop distribution data of the piccolo through actual engineering tests. The experimental results show that when the bleed air flow is the same, the higher the inlet temperature is, the higher the pressure and temperature along the piccolo section are, and the pressure drop changes significantly, while the temperature drop in the rear section of the piccolo section is small. When the inlet temperature is the same, the smaller the bleed air flow is, the lower the pressure and temperature along the piccolo section are, the pressure drop changes smaller, and the temperature drop in the rear section of the piccolo is greater. Finally, this paper compares and analyzes the test results with the model calculation data, and further verifies the correctness of the model calculation. The test platform for the flow distribution of bleed air anti-icing system of aircraft wing on the ground built in this paper can provide a reference for the optimization design of bleed air anti-icing system of aircraft wing.