Computational Analysis for Different Sorts of Vortex Generator Over Aircraft Wing
Keywords:
Aerodynamic Efficiency, Boundary layer, Flow separation, Stall reduction, VG - Vortex generator.Abstract
The continuous focus of flight aerodynamics mainly falls to enhancethe aerodynamic characteristics and maneuverability of the
aircraft. Thisenhancement includes the reduction of drag and stall phenomenon. The airfoil which contains vortex generator will have
comparatively less drag than the plain airfoil.Introducing Vortex generator on the aircraft wing will create turbulence by creatingvortices which delays the boundary layer separation resulting in decrease ofpressure drag and also increase in the angle of stall. In addition, wake reductionleads to reduction in acoustic emission. The overall objective of this paper is toimprove the aircraft maneuverability by delaying the flow separation point at stall and thereby reducing the drag by applying the Vortex generator effect over theaircraft wing. This project includes both computational analysis ofvortex generator on aircraft wing, using NACA 0018 airfoil. Vortex generator of triangular delta, semi-sphere, hexagon, cylinder, square is selected for the analysis; airfoil istested under the inlet velocity of 30m/s and 60m/s at different angle of attack (5˚, 10˚, 15˚,20˚, and 25˚). This analysis favors the vortex generator by increasing L/D ratio andthereby providing the maximum aerodynamic efficiency, which provides the enhanced performance for the aircraft.
