A method for high-lift turbine blade design based on Pritchard 11 parameters method was introduced for turbine nozzle guide vane working under low entrance Mach number and typically low lift at front part of the blade. A series of high lift nozzle guide vane profile were designed and investigated using numerical calculation

and validated by linear cascade test. Results showed that the blade loading of high-lift profile was more uniform due to increase of Mach number at front part of the suction side

and the throat suction moved forward. The Mach number characteristic and attack angle characteristic showed that the highly-loaded blades generated lower total pressure loss. The pressure loss coefficient of high-lift profile was 259% lower under design condition than that of the datum profile.