Investigating the effects of induced vortices on airplane wing aerodynamic performance using ZnO nanostructure

Abstract

The need for revolutionary techniques to augment aerodynamic efficiency is paramount for achieving substantial reductions in drag and consequent fuel consumption. This paper revolves around exploiting zinc oxide nanostructures to increase boundary layer adhesion and delay stall in airfoils. Zinc oxide nanostructures are employed to induce vortices, re-energize the airflow and function as nano flow control device. The work on this paper commenced with the proof of concept by means of comprehensive computational simulation utilizing COMSOL software and ended with experimental lab tests. A meticulous two-step process involving the sol–gel method and dip coating was employed to grow nanorods on the wing’s surface. Initial prototyping utilized 3D printing, and subsequent aluminum samples were produced using sand casting techniques. The coated wing specimen underwent rigorous wind tunnel testing to assess its aerodynamic performance under controlled airflow conditions. This thorough approach facilitated a profound understanding of the coated wing's behavior, enabling insights for further optimization. The results revealed a significant 16% delay in stall and an average 4% reduction in drag. This pioneering approach not only optimizes aircraft aerodynamics but also mitigates fuel costs and environmental impact. Moreover, the study's observations offer avenues for future exploration, including the fine-tuning of coating parameters and exploring diverse applications of ZnO nanorods in aerospace engineering.