Annotation

Annotation: For the design of an aircraft wing, algorithms are required to determine the geometric parameters of the designed lifting surface in order to provide the necessary values of integral design parameters that significantly affect flight performance. In this paper, methods for creating metamodels for problems of aerodynamics based on the approximation of data from numerical experiments are investigated. The use of these methods significantly reduces the time spent on searching for optimal geometric characteristics of the wing, bypassing long-term experimental studies on the influence of geometric parameters on the power characteristics of the considered lifting surface. The aircraft development process consists of several stages, the most important of which is the preliminary design, at which stage a decision is made on the viability of the aircraft development project. The first stage is to develop a variant of the geometry of the aircraft, based on expert experience, then the calculation of the main aerodynamic configuration parameters is carried out taking into account various flight conditions using software tools and engineering methods. Experimental data obtained as a result of testing an aircraft model in a wind tunnel is one of the important sources of information about aerodynamic properties. The third stage consists in a detailed analysis of the obtained flight characteristics of the aircraft. Currently, the aviation industry needs to move to a new technological approach based on the use of software for automated optimal design of aircraft aerodynamics, taking into account their design features and limitations. Parametric modeling in specialized computer-aided design systems allows you to speed up the process of generating technical proposals. Making design decisions is an important stage, the purpose of which is to choose one of the possible options for the values of the geometric model parameters. This choice is usually a compromise, as each option has its advantages and disadvantages. In this paper, a method for constructing a surrogate model based on the kriging interpolation method is developed. The proposed model makes it possible to analyze complex multiparametric problems of aerodynamics. Using the example of the problem of two-dimensional flow around an airfoil, nonlinear relationships of the main aerodynamic characteristics with the geometric parameters of the profile at different speeds of the incoming flow were found.