Substantiation of choosing rational appearance of nose of aircraft with the use of mathematical modeling

As part of this work, a comprehensive analysis of the question of ensuring the specified aerodynamic performance of the aircraft required to implement a cruising supersonic flight at M ~ 1.5. B Analysis of possible methods of aerodynamic performance evaluation (AP) of aircraft components in the course of optimization of their geometrical parameters to achieve a minimum contribution to the AP. The paper presents an algorithm for the formation of the nose part of the aircraft of minimal aerodynamic resistance, and also selects criteria for evaluation of the nose part of the aircraft as an element of the glider, which has a significant contribution to the overall aircraft AP at a flight speed of M > 1 . The results of this work can be used at the early stages of aircraft tying up to reduce the time required for the formation of a mathematical model of the surface of a prospective aircraft.