Numerical studies on aerodynamic performance of NACA 0018 profile in fundamental and research application of the aerospace industry

Abstract

For a good functioning of the activities carried out within research institutions both at managerial level and for fulfilling the technical requirements, we aim to determine the aerodynamic characteristics of the standard profiles used in the aerospace field by testing in the subsonic tunnel. We also intend to conduct a study based on numerous experimental tests performed in wind tunnels that can be compared to the actual scale of the aircraft for structural integrity and improving its performance. The purpose of this paper is to evaluate the dynamics of fluid separation, lift and drag. This allows us to further improve the profiles so that it is essential to improve the efficiency and performance of an aircraft in terms of improving lift and reducing drag. In the present research, numerical and experimental studies are performed on a finite geometry of the NACA0018 wing at different angles of attack and Reynolds numbers. This paper aims to improve the performance, accuracy and quality of testing, increase the competitiveness of similar installations on the world market, ensure the national research and development capacity of new products in the aeronautical and defense industry.