The study determined the aerodynamic characteristics of the helicopter rotor in consideration of the interaction with the fuselage and the fixed surfaces

1. Building the non-linear mathematical model to determine the aerodynamic characteristics of the helicopter rotor by the discrete vortex method with quadrilateral vortex elements, applying the vortex diffusion model.
2. Determine the aerodynamic characteristics of the helicopter rotor in consideration of the influence of the fuselage and fixed surfaces by the discrete vortex method.
3. Proposing an approach using the discrete vortex method with quadrilateral vortex elements to simulate the airflow over the 3D object.
4. There are new contributions in building mathematical models for studying aerodynamic interaction between components in the multi-body system by the discrete vortex method. On that basis, creating a flexible calculation tool, ensuring accuracy.
5. Contributing to improving the efficiency of helicopter operation and exploitation. The research results of this thesis serve well for other scientific research projects.