In order to analyze the distribution of the tail flow field during the take-off and landing ground taxiing phase, based on computational fluid dynamics (CFD), a foreign high-speed aircraft numerical model was studied, based on Delaunay unstructured triangulation mesh generation method, 3D Reynolds averaged N-S equation, Realizable k-ε turbulence model and ROE discrete scheme are used to simulate the external flow field of the whole aircraft by coupling hide alorithm. The tail pressure field, temperature field and velocity field are analyzed under the condition of sliding at 7° angle of attack and considering the ground effect and tail jet. The results show that the pressure in the wake decreases in the axial and transverse directions, while the temperature and velocity decrease in the axial direction and double peak in the transverse direction.