Experiments are being conducted in the 1.5m low speed wind tunnel to provide the required data for the design of the NAL Regional Transport Aircraft (RTA). In the first phase, pressure measurements have been conducted in the velocity range of 25-45 m/s and incidence angle range of -4 to 16 deg on the reference airfoil NASA 0416 and on the airfoil NAL 7025, designed for the RTA wing. The results show that our measurements compare well with those from NASA. The coefficients of pressure and lift show that the NAL 7025 airfoil has promise for being adapted for the RTA
