This paper presents selected issues regarding the design of a complex object of a turbine jet engine inlet duct model for the purposes of numerical analysis of the phenomenon of inlet vortex formation. The authors described the process of discretisation in the matter in question and presented certain guidelines for preparing and conducting discretisation of the computational area. The authors presented an example test findings analysis to verify the accuracy of the object's shape, computation grid and the selection of the boundary conditions and solution algorithm. The main part of the paper regards analysis of changes in the location of the vortex (point of stagnation) based on an examination of the impact of changes in the velocity and inlet and gust angles. The authors seek to determine areas and regularity of points of stagnation