Abstract: The experiment method for studying the hot air antiicing system of inlet guide vane was introduced. Some antiicing tests were performed in different external icing flow conditions. In experiments, the blade surface temperature change was measured by thermalcouples thermal couple and the experiment process was recorded by an image recording system. The experiment results show that the ice accretion is located at the leading edge and suction side, and the guide vane internal hot air channel should be designed efficiently in the hot air antiicing system to improve antiicing performance.