Abstract: An analysis of the aircraft skin temperature field of the physical mechanism and the establishment of the aircraft skin temperature coupling calculation of the theoretical model were presented. A more complete factor of the various sources of heat on the surface skin of the aircraft was considered, including the aerodynamic heating, hot engine parts and various parts of the conduction, convection and radiation each other. Thus, the calculation model of three-dimensional flow field coupled with the solid wall was developed: skin used in solid-wall heat conduction model, and skin on atmospheric radiation used discrete ordinate method (DOM). Finally, the finite volume method and RNG k-ε turbulence model were employed to solve N-S equation. By numerical calculation method, the external and internal environment coupled heat transfer on aircraft skin was studied. The results show that the methodology is appropriate for numerical simulation of aircraft-skin temperature field.