Abstract: Some calibrations and tests were conducted in a movable icing wind tunnel to study the test methods for cloud calibration, icing test, anti-icing and de-icing test, and to enable its usage on the ground anti-icing test of aircraft air intake system. The water cooling distance was determined by the comparison of the ice shapes on metal cylindrical tubes. The cloud uniformity was measured by an icing grid. The droplets media volume diameter and the liquid water content were measured by Cloud Calibration Probe. Besides, an engine nacelle lip model and a NACA23012 wing model were both used in the icing test, anti-icing and de-icing test investigation. The results show that the movable icing wind tunnel test can present general icing law with the influence of various factors. Although environmental factors have a great effect on simulated outdoor icing test conditions, the present method is capable of applying the anti-icing test for an aircraft air intake system.