Understanding the sensitivity of film cooling to a range of inlet conditions is necessary when verifying the robustness of a cooling design. In order to do this, adiabatic and overall effectiveness data were measured at various blowing ratios on an airfoil with nine shaped hole rows. This was performed in a low-speed linear cascade at two incidence angles, an inlet Reynolds number of 120000, a turbulence intensity of 5%, and a density ratio of 1.23. The test section was first adjusted so that the airfoil pressure distribution and stagnation line matched a CFD model. Infrared thermography was then used to measure effectiveness levels. This process was then repeated for the second incidence angle. Airfoil inlet pressures for each blowing ratio were matched between incidence angles. The stagnation line position changed the laterally averaged adiabatic effectiveness by as much as 0.2 near the showerhead. The effect persisted strongly 35 hole diameters downstream of the stagnation row but was visible over the whole viewable area of 160 diameters. The showerhead was then investigated in detail and it was found that the stagnation line dramatically increased the near-hole adiabatic and overall effectiveness levels when positioned within the breakout footprint of the stagnation hole row. This is the first study to present measured effectiveness values over both the pressure- and suction-sides of a fully-cooled airfoil for appreciably off-nominal incidence angles as well as examine adiabatic and overall effectiveness levels for a conical stagnation row of holes.