SUBSONIC PROFILES FLOW
The numerical modeling of an in viscid flow of plane wing profiles in up to sound operational modes is considered. The complexity of aerodynamic processes with possible circulating zones of a separation of a boundary layer requires qualitative calculation with the purpose of deriving the improved designer wing performances. The used finite difference scheme with decomposition of a difference operator on space and physical processes precisely approximates the initial continuous task. The numerical score is carried on in physical space with a consequent transformation of coordinates in calculated rectangular area before installation on time and exit on a fixed flow regime. The results of numerical experiment for pressure coefficient are considered.