Local and average heat/mass transfer coefficients have been measured on the tip of a simulated gas turbine blade using the naphthalene sublimation technique. The tip of the blade is coated with a layer of naphthalene and mass transfer coefficients are measured after exposure to the flowin a wind tunnel. The heat/mass transfer analogy can be applied to obtain the corresponding heat transfer coefficients. The experiments have been conducted using a five blade linear cascade with a blade centered configuration. A flat tip blade with the profile of a first stage rotor blade of a high performance aircraft engine is used. Measurements are taken using a tip clearance level of 1.1% of chord and an exit Reynolds number based on chord of approximately 7.2×10⁵. Flow visualization has been performed on the tip surface using an oil dot technique and results are compared with the mass transfer data. The presence of a separation bubble by the pressure side corner is evident. The flow that separates at the gap entrance impinges on a line parallel to the pressure side rim, strongly enhancing the heat/mass transfer in this location. Low mass transfer coefficients are measured in the leading edge region of the blade.