Numerical analysis of a swept wing hot air ice protection system

Abstract

A tight-coupling heat transfer method is proposed in this paper for the analysis of the performance of the hot air ice protection system. The Eulerian method is used for the calculation of the local collection efficiency. The external heat transfer coefficient was computed using the boundary layer integrated method. The thermal conductivity within the wing skin and the internal heat transfer between the hot air flow and the skin were computed using the computational fluid dynamic method. At the same time, the external heat flux boundary condition and the surface temperature were updated automatically by user-defined function to drive the iteration of the tight-coupling heat transfer calculation. The surface temperature results in dry air condition are compared with flight test data and show agreement. The maximum temperature difference between the simulation and the test is 11.5 K. In addition, the method proposed in this paper is applied to the wing hot air ice protection system of a real aircraft in icing conditions. It is found that the surface temperature ranges from 3 to 30 ℃ under certain flight and icing conditions. Larger droplet diameter or larger liquid water content leads to more runback water which changes the surface temperature not much when the parameters of the bleeding air are the same.