Numerical Optimization of the Wing Trailing Edge Mechanization Position of Transport Category Aircraft in the Landing Configuration

Aeronautical and Space-Rocket Engineering


Аuthors

Berezko M. E.1, 2*, Shevyakov V. I.2**

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. PJSC Yakovlev , 68, Leningradskiy prospect, Moscow, 125315, Russia

*e-mail: maxberezko@yandex.ru
**e-mail: shevvi@mail.ru

Abstract

Solving numerical optimization problems while aerodynamic design is a modern and up-to-date tool of aircraft engineering performance characteristics ensuring specified in the terms of reference. Computation and analysis of options multitude by computer modeling can significantly minimize design costs by reducing the number of expensive wing-tunnel experiments.
One of the urgent optimization tasks consists in optimizing the wing airfoils shape and position of the high-lift wing airfoils constituent parts, such as flaps, slats and the basic part of the airfoil. Application of various optimization algorithms allowed clarifying the effective shape or position of mechanization without a pipe experiment and empirical techniques.
The article presents the results of numerical optimization of the flap position of a high-lift wing airfoil for landing mode. The values of the gap, overlap and deflection angles of the airfoil flap and rear part were selected as variable parameters. Basic aerodynamic characteristics of both initial and optimized wing profiles in the landing configuration were obtained with the numerical simulation. The authors give the effectiveness estimation of the optimization method being employed while the wing high-lift airfoils in landing configuration design.
Numerical simulation of the flow-around was accomplished with the ANSYS FLUENT software. A system of Reynolds averaged Navier-Stokes equations closed by the Spalart-Allmaras turbulence model was being solved. Numerical problem of the airfoil flow-around by a viscous compressible turbulent gas (air) is being solved in a stationary formulation. The computational grid consists predominantly of rectangular elements with near-wall prismatic layer.
Methods recounted in the article allow achieving optimal position of the airfoil trailing edge mechanization to ensure the best aerodynamic characteristics at the landing mode.

Keywords:

high-lift airfoil, takeoff-and-landing configuration, genetic algorithm, Multi-Objective Genetic Algorithms (MOGA)

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