Abstract:

An icing wind tunnel supercooled large droplet icing test was carried out to verify the design criteria of a hybrid wing. The test conditions adopt the combination of large and small water drop nozzles to achieve the “double peak” distribution characteristic. The NACA0012 airfoil with a chord length of 0.50 m is used as the original airfoil， and the hybrid wing design criteria for engineering and airworthiness are employed to design the hybrid wing. The Navier-Stokes （NS） equation is used to calculate the airfoil pressure distribution with the goal of overlapping the stagnation point position of the hybrid wing with the original airfoil and the suction peak at the leading edge as much as possible. The designed chord length of the hybrid wing was shortened by 50%. The design effect of the hybrid wing was verified by the icing wind tunnel supercooled large droplet icing test. The ice shape characteristics of the original airfoil and the hybrid airfoil model are basically the same， and the ice height of the hybrid airfoil model is slightly higher. It was verified that the design criteria of the hybrid wing are still suitable for the icing wind tunnel supercooled large droplet icing test， providing technical support for the follow-up of the supercooled large droplet icing wind tunnel test of related civil aircraft models.

Key words: supercooled large droplet, hybrid wing, airfoil design, icing wind tunnel tests, aircraft icing