Parametric optimization methods in a transonic transport aircraft characteristic wings airfoils designing problem


Аuthors

Panteleev A. *, Gunchin V. K.**, Nadorov I. S., Akhmedov I. A., Silaev N. A.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: avpanteleev@inbox.ru
**e-mail: gunchinvk@mai.ru

Abstract

An approach to designing aircraft wing airfoils based on the use of metaheuristic global optimization algorithms is proposed. At the first stage of the project, the wing planform is determined, which is characterized, first of all, by such parameters as the quarter-chord sweep angle, taper ratio, aspect ratio, and the shape of the rear and front extensions (if any). In addition, the average relative thickness of the wing is specified to ensure the required strength characteristics of the structure, as well as the required internal volumes. Thus, when choosing the wing planform and wing average relative thickness, the team of designers and engineers must find optimal solutions that satisfy the conflicting requirements for achieving high values of aerodynamic and weight characteristics along with taking into account the specified design limitations. Next, the design of airfoils is carried out, which are then used to create a wing shape. The wing is formed by four sections from airfoils with specified thickness-to-chord ra-tio. Bernstein polynomials are used to parameterize the airfoil geometry, and a soft-ware system implementing the solution of the Navier-Stokes equations is used to cal-culate its aerodynamic characteristics. A design scheme based on consistent mathe-matical modeling of the flow process and parametric optimization is developed. The optimization methods used were a modification of the moth-flame optimization algo-rithm and Luus–Jaakola method with successive reduction of the feasible solutions set. It is demonstrated that as a result of applying the proposed approach, the initial airfoils specified by the designer can be changed in order to obtain the required values of the aerodynamic characteristics. Numerical results confirming the effectiveness of the approach are presented.

Keywords:

wing airfoil design, airfoil parameterization, wing polar, metaheuristic optimization algorithms, mathematical modeling, optimization methods

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