Open AccessXFOIL analysis on low reynolds number airfoil
Author(s) -
Yagya Dutta Dwivedi,
Pabbu Pavithra,
Emmadi Parimala,
Yalavarthy Meena
Publication year - 2022
Publication title -
graduate research in engineering and technology
Language(s) - English
Resource type - Journals
ISSN - 2320-6632
DOI - 10.47893/gret.2022.1082
Subject(s) - airfoil , reynolds number , aerodynamics , lift induced drag , lift (data mining) , lift coefficient , aerospace engineering , aerodynamic center , lift to drag ratio , angle of attack , drag divergence mach number , mechanics , drag , physics , computer science , pitching moment , engineering , turbulence , data mining
The range of low Reynolds number airfoil is between 104 to 105.In this study the investigated airfoil is NACA2414. The aerodynamic performance of low Reynolds airfoil is less than 105 is important for various applications such as unmanned air vehicles, Micro air vehicles and low-speed/high altitude aircrafts. In general, the lift and drag characteristics of most of the airfoils cannot be assumed constant having Reynolds number less than 106. XFLR5 is an analysis tool for airfoils, wings and planes operating at low Reynolds numbers. It includes XFOIL’S direct and inverse analysis capabilities. Wing design and analysis capabilities based on the lifting line theory, on the vortex lattice method, and on 3-D panel method. The pressure distribution (cP)and lift coefficient (cL) are important parameters that characterize behavior of the airfoils. Pressure distribution information is the foundation of aerodynamic analysis during aircraft development.