Proper cooling of the airfoil trailing edge is imperative in gas turbine designs since this area is often one of the life limiting areas of an airfoil. A common method of providing thermal protection to an airfoil trailing edge is by injecting a film of cooling air through slots located on the airfoil pressure side near the trailing edge, thereby providing a cooling buffer between the hot mainstream gas and the airfoil surface. In the conventional designs, at the breakout plane, a series of slots open to expanding tapered grooves in between the tapered lands and run the cooling air through the grooves to protect the trailing edge surface. In this study, naphthalene sublimation technique was used to measure area averaged mass/heat transfer coefficients downstream of the breakout plane on the slot and on the land surfaces. Three slot geometries were tested : a) a baseline case simulating a typical conventional slot and land design, b) same geometry with a sudden outward step at the breakout plane around the opening, and c) the sudden step was moved one-third away from the breakout plane in the slot. Mass/heat transfer results were compared for these slots geometries for a range of blowing ratios (M=(pu)(s)/(pu)(m)) from 0 to 2. For the numerical investigation, a pressure-correction based, multi-block, multi-grid, unstructured/adaptive commercial software was used in this investigation. Several turbulence models including the standard high Reynolds number k-epsilon turbulence model in conjunction with the generalized wall function were used for turbulence closure. The applied thermal boundary conditions to the CFD models matched the test boundary conditions. Effects of a sudden downward step (Coanda) in the slot on mass/heat transfer coefficients on the slot and on the land surfaces were compared both experimentally and numerically.