Unmanned air vehicle 3-D wing aerodynamical design and algorithm stability with respect to initial shape

Abstract

A new technology of the optimal design of aerodynamic configurations based on a new generation software product is used for aerodynamic design of a 3-D wing of the middle class unmanned aerial vehicle. The optimal shape of the wing, which is characterized by minimum total drag at a fixed lift coefficient and corresponding to the specified geometric and aerodynamic constraints, is determined on the basis of the global search method and numerical solutions of the complete Navier-Stokes equations. It is shown that the proposed approach provides reduction in a wing drag in the cruise flight zone and significantly reduces the material and time costs for aerodynamic aircraft design. Optimal wing has a significantly lower drag at the main design point, and it can be used during cruising and in its vicinity. Optimization allows improving of the glider wing quality. Optimal wing is distinguished by better aerodynamic characteristics in the wide vicinity of design point in terms of the Mach numbers and lift coefficient. Such wing is resistant to the small changes in the flight conditions and it meets all given geometric and aerodynamic constraints.