A numerical model is developed to quantitative evaluation of the thermal and structural characteristics of the regenerative cooled scramjet engine. The three-dimensional internal CFD platform for scramjet and the computational program of domestic aviation kerosene properties are incorporated together to develop three dimensional thermal evaluation code. Then the thermal evaluation results from the code can be introduced into the thermal-stress finite element program to complete quantitative structural analysis of engine structure. The results show the temperature and heat flux distribution of the scramjet structure is very uneven. Local plasticity occurs in some areas. The results of this paper can be an valuable reference for the test and design of regenerative cooled scramjet.