ON MODERN APPROACH TO AIRPLANE-TYPE UNMANNED AERIAL VEHICLES DESIGN WITH SHORT TAKEOFF AND LANDING PART III. NUMERICAL MODELING OF AIRCRAFT VORTEX AERODYNAMICS BY DISCRETE VORTEX METHOD

Abstract

This publication continues a series of review papers devoted to the urgent problems of designing unmanned aircrafts of the next generation, which are expected to appear in the period from 2025 to 2035. The paper considers simple and effective numerical methods based on the ideas of a vortex lift surface that allow for performing a full parametric analysis of aircrafts with very complex aerodynamic shape of the wing. Calculation examples are given for triangular wing of small and moderate aspect ratio with an acute and rounded leading edge, as well as a wing of complex shape. We consider design methods for deformed aerodynamic surfaces with optimal properties and a method for wing mechanization calculating. The formation of vortices on sharp front edges, the destruction of vortices over the wing surface and diffusion mechanism of vortices are studied. The calculation method for small aspect ratio wings is described. The results obtained are compared with the results of the experiment and numerical verification.

Keywords

• national technological initiative
• aeronet
• unmanned aerial vehicle
• vertical take-off and landing
• short take-off and landing
• aerodynamics
• discrete vortex method
• slender-delta wing
• vortex lift