The optimization method for aerodynamic shape profiling of the airframe and the engine elements of a high-speed flying vehicle is presented. The cruise lift is considered as the objective function. Optimization is performed under external dimensions and pitching moment constraints. Flow fields are modeled within the framework of 2D Euler equations system. Integral and local aerodynamic characteristics of optimal configurations are analyzed. The balancing effect of the flying vehicle on the optimal geometry is investigated.
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