METHOD OF OPTIMAL AERODYNAMIC DESIGN OF THE NACELLE FOR THE MAIN PROPULSION SYSTEM WITH A HIGH BYPASS RATIO

摘要

An algorithm of optimal aerodynamic design of the contour of the main propulsion system nacelle for a subsonic airliner, which is based on numerical methods used for solving the Reynolds-averaged Navier-Stokes equations, is proposed. The use of methods of conditional optimization of a multifactor function makes it possible to form an aerodynamically efficient nacelle contour under the condition of a large number of aerodynamic and structural constraints. The capabilities of the proposed technique are illustrated by results of optimization of the shape of an isolated nacelle of the main propulsion system with a high bypass ratio designed for a mid-range passenger airliner.