The concept of Delta wings emerged in response to meet the need of obtaining superior performance from wing configurations at high speeds. The flow over a delta wing is a vortex dominated flow field. The aerodynamic characteristics depend on the structure of primary and secondary vortices over the wing. The delta wing owes much of the lift that it is able to generate at subsonic speeds to the fact that the flow separates at the leading edge of the wing. At high angles of attack (AoA), a phenomenon known as vortex breakdown occurs in the vortices above the wing. Vortex breakdown results in the destruction of the tight and coherent vortex.In this study the Second International Vortex Flow Experiment (VFE-2) 65° sweep delta wing model was used. The soild model is generated using Solid works.Numerical analysis using commercially available ICEM CFD and Fluentis done to simulate the flow field over the65° sweep angle sharp edged delta wing.The numerical results obtained is validated with the experimental results obtained by Chu and Luckring [6].After validation, the effect of AoA on the vortex generation is studied and an location of the vortex breakdown position is determined. © Research India Publications.