Abstract: The icing and anti-icing process of the aero-engine is complex, which can not be simulated accurately by numerical calculation. As a result, experiment is an indispensable means for the engine research. The first large-scale icing wind tunnel of our country has been built, which has the capacity to carry out icing tests on the aircraft wing section. But further development of the icing and anti-icing test technology is needed to meet the requirement of the next stage model designing and airworthiness certification for aero-engines in our country. Supported by the 3 m×2 m large-scale icing wind tunnel, the inlet gas simulation technology and hot-air supply technology were developed first, then a set of test procedures and methods was put forward, and finally the icing wind tunnel test for the inlet part of an aero-engine was carried out. The results indicate that the system can simulate the internal and external flow coupling of the engine and the anti-icing state of the compressor. The procedures and method of icing wind tunnel test are reasonable and feasible, and the test dynamic process and the flow field pressure in the inlet are successfully measured. It provides a technical support for the design of ice protection system and the verification of airworthiness on aero-engines.