The influence of incidence angle on film cooling effectiveness is studied for a cutback squealer blade tip. Three incidence angles are investigated 0 at design condition and 5 at off-design conditions. Based on mass transfer analogy, the film cooling effectiveness is measured with pressure sensitive paint (PSP) techniques. The film cooling effectiveness distribution on pressure side near tip region, squealer cavity floor and squealer rim tip is presented for the three incidence angles at varying blowing ratios. The average blowing ratio is controlled to be 0.5, 1.0, 1.5 and 2.0. One row of shaped holes are provide along the pressure side just below the tip; two rows of cylindrical film cooling holes are arranged on the blade tip in such a way that one row offset to the suction side profile and the other row is along the camber line. The pressure side squealer rim wall is cut near the trailing edge to allow the accumulated coolant in the cavity to escape and cool the tip trailing edge. The internal coolant-supply passages of the squealer tipped blade are modeled similar to those in the GE-E3 rotor blade. Test is done in a five-blade linear cascade in a blow down facility with a tip gap clearance of 1.5% of the blade span. The Mach number and turbulence intensity level at the cascade inlet was 0.23 and 9.7%, respectively. It is observed that the incidence angle affects the coolant jet direction on the pressure side near tip region and blade tip. The film cooling effectiveness distribution is altered. The peak of laterally averaged effectiveness is shifted to upstream or downstream depending on the off-design incidence angles. The film cooling effective inside the tip cavity can be increased up to 25% with the positive incidence angle. However, in general, the overall area averaged film cooling effectiveness is not significantly changed by the incidence angles in the range of study.