In order to eliminate the constrains of engine icing test on experimental ability and space

an icing scaling law of turbofan engine nacelle icing test was established based on similar requirements such as the airflow field

water droplet impingement and ice accretion characteristics. And there were three airflow velocity selections based on airflow Reynolds number

airflow Weber number and water droplet Weber number respectively

and these three velocity selections can be used to reflect different influencing parameters on icing similarity. The glaze and rime ice accretion conditions of 1/2 sub-scale turbofan engine nacelle model were obtained by this scaling law. And the ice prediction on turbofan nacelle inlet was carried out with numerical simulation

and the similarities of water droplet impingement

ice accretion and runback water characteristics were analysed. Results show that the scaling law based on airflow Weber number and water droplet Weber number can better ensure the similarity of the droplets impingement on the surface of the scale model and the reference model under the glaze ice and rime ice conditions

and the similarity is not affected by the freezing temperature. The variation and limit of the runback water is similar to the reference model. Under different icing conditions

the surface ice accretion of scale model is similar to the reference

and this scaling law can provide a good basis for the subscale nacelle icing test.