An approach to determining the rational shape of the nose of a supersonic aircraft using mathematical modeling methods

At the initial stages of designing a supersonic aircraft, numerical modeling of the flow process of the assumed aerodynamic forms is performed. This allows you to significantly reduce the time and financial costs of field testing. When modeling, you can get all the parameters of the process, but only some of its values are obtained during the experiment. This becomes especially relevant for modeling the flight conditions of a supersonic aircraft. This paper shows a comprehensive approach to solving the problem of providing the specified aerodynamic characteristics of the aircraft required for cruising supersonic flight at M ~ 1.5. The article analyzes the proposed methods for evaluating the aerodynamic characteristics (ADC) of aircraft components in the course of optimizing their geometric parameters in order to achieve a minimum contribution to the ADC. The paper presents an algorithm for forming the nose of the aircraft with minimal aerodynamic drag, and also selects criteria for evaluating the ADC of the nose of the aircraft as an element of the airframe that has a significant contribution to the ADC of the aircraft as a whole at a flight speed of M > 1. The results of these studies can be used at the early stages of design, this will reduce the time for forming a mathematical model of the surface of a promising aircraft (LA).