The issue taken into consideration is sudden increase in drag over an aircraft wing due to three dimensional flow, tip vortices and flow separation. When flow separates its displacement thickness increases sharply this modifies the outside potential flow and pressure field. The pressure field modification results in an increase in pressure drag, and if severe enough will also result in loss of lift and stall. This study presents computational analysis results of a prototype wing with and without vortex generators of two different shapes located at leading and trailing edges of a linear wing. Here both wind tunnel testing and computational fluid dynamic analysis is carried out. The effect of the vortex generators are studied in four different cases. Nine sets of rectangular shaped vortex generators inclined at 15 degree were placed in the leading edge and trailing edge of the wing, nine sets of ogive shaped vortex generators inclined 15 degree were placed in the leading edge and trailing edge of the wing, are the cases analyzed. The studies also focus on prevention of downstream flow separation and improve overall performance by reducing drag. Both analytical and experimental results are compared where it shows that the pressure over the upper surface increases, so that the boundary layer is reenergized and attached with the body surface thus reducing the drag.
Keywords — ANSYS, CATIA, Ogive Vortex Generators