Abstract
Based on numerical studies of a high-speed business jet aerodynamic layout, the influence of the bypass ratio of turbojet engine nacelles on the flow features, pressure distribution, and aerodynamic characteristics of the aircraft is considered, in which the interference of the nacelles with an airframe is taken into account. The estimation of the increase in flight range with an increase in the bypass ratio at the constant wing geometry is accomplished. The influence of increasing the engine bypass ratio on the wing section, when its middle surface changes to reduce the harmful interference of the engine nacelle and airframe, is shown. It was found that the optimization of the aerodynamic configuration of the wing while maintaining its relative thickness does not significantly affect the optimal bypass ratio, which for the considered airplane layout does not exceed m ~ 9.6.
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