Валідація математичної моделі дослідження аеродинамічних характеристик гвинтовентилятора

This article presents the stages and results of the mathematical model validation of an eight-bladed propeller fan. This study investigates the dependence of the thrust coefficient on the power coefficient of the propeller fan at the specified sizes of the calculation spaces (domains), number of calculation grid elements, and selected turbulence model. The object of the study is an eight-bladed propeller fan with specified blade profile installation angles on the control section. The purpose of this study is to select and justify the parameters and settings of the calculation mathematical model of the propeller fan. The following tasks were solved to achieve the goal: a solid-state model of the known eight-bladed propeller fan of the SR7L type was built; several calculation areas and grids were created for mathematical modeling by the numerical method; calculations were performed with different model settings and the results obtained were compared with known experimental data. Model validation, i.e., confirmation of the characteristics of the propeller fan, was carried out in three stages by sequential selection: the size of the computational space, the number of elements of the computational grid, and the type of turbulence model in the first stage. The simulation results showed that the sequential selection of parameters and settings of the computational mathematical model of the eight-blade propeller fan and comparison of the obtained simulation results with experimental data allowed us to justify the rational value of the size of the computational space (4D x 4D x 8D), the computational grid number of nodes (7.0 million) and the type of turbulence model - GEKO - 2.5 Re-γθ. The maximum relative error of the simulation results does not exceed 3.5% relative to known data. The scientific novelty and practical significance of the results lies in obtaining recommendations on the parameters of a numerical experiment when modeling the flow around a turbojet engine propeller fan.