Comparative Computational Investigation of Aerofoil Performance with and without Vortex Generators

Abstract

Abstract

Aircraft with an efficient aerodynamic design is a major concern in current aerospace industries trends, but the flow separation has been playing a predominant role in the aircraft performance reduction and thereby affecting the aerodynamic efficiency. To overcome these problems, vortex generators (vortilon) are fixed on the upper surface of the wing. This paper focused on the aerodynamic performance analysis of available NACA-23012 aerofoil with and without Vortex Generators, for different aerodynamic conditions in order to optimize the VG location and its advantages. Also to improve the performance of the aircraft, delay boundary layer separation, increase in the stall angle and thereby increase in the lift forces. The reference component of this paper has been designed and discretized using ICEM-CFD and to analyze the performance of NACA 23012 aerofoil with and without VG, Ansys Fluent is used.

Keywords: Boundary layer, Canard wing, Numerical Simulation, Vortex Generator

Cite this Article

Naveen Kumar K, Vijayanandh R, Varun S et al. Comparative Computational Investigation of Aerofoil Performance with and without Vortex Generators. Journal of Instrumentation Technology & Innovations. 2018; 8(2): 1–16p.