BOUNDARY LAYER STATE INFLUENCE ON START OF THE INWARD-TURNING INTAKE

摘要

CFD and EFD studies of the flow in the air intake device of the high-speed civil aircraft model HEXAFLY-INT have been performed.It was shown that the characteristic feature of this intake is the occurrence of subsonic separation zone in the central part of flow.Boundary layer on the intake compression surface influences essentially on the development of the separation zone downstream. The turbulent boundary layer in this case is more preferable than laminar one. Right selection of the turbulence generators makes it possible to improve substantially the intake characteristics.