Computational Analysis Over NACA-23015 Airfoil for Flow Separation Delay using Passive Flow Separation Techniques

Boundary layer is the layer of fluid in the immediate vicinity of a boundary surface where the effects of viscosity are significant. It is a thin layer of flowing gas or liquid in contact with a surface such that of an airplane wing or the inside of a pipe. Boundary layer separation is the detachment of a boundary layer from a surface into a wake. Separation occurs in flow that is slowing down, with pressure increasing, after passing through the thickest part of a streamline body, for example. A theoretical study on flow separation delay which involves methods using passive flow separation delay techniques is studied in this report. This report reviews the suction control over boundary layer method in depth there by making it easy to understand controlling of boundary layer separation. Analysis on Flow separation delay over NACA-23015 airfoil are conducted by varying velocity and Slots placement along the chord. This work helps further researchers in identifying and selecting the best position for suction Slots for better aerodynamic properties in designing a wing.