Integrated modeling method of the internal and external flow of helicopter/inlet

Abstract

The internal and external integrated flow field modeling method of the helicopter/inlet system was studied. The boundary of internal flow field modeling was proposed. The internal and external integrated calculation model, including the helicopter fuselage, rotor, tail rotor, and other rotating components, as well as the internal flow field of the inlet, was established. On this basis, numerical calculation is carried out according to typical working conditions to analyze the flow field characteristics in the forward flight state and the influence of inlet back pressure on performance parameters. The results show that the integrated numerical calculation model established in this paper considers the internal and external interference of the actual rotor movement in the outflow field. The integrated flow field calculation in typical working conditions shows that the occlusion of the rotor blade and the fuselage will cause interference with the inlet flow field. The parameters of the left and right inlet ports will be different. With the decrease of inlet back pressure, the total pressure recovery decreases with the increase of flow rate and is obviously lower than that without rotor interference.