The stator and rotor blade hub sections designed for a high
pressure turbine stage were studied in detail for their
aerodynamic and heat transfer characteristics . The profile
sections were tested in the National Aeronautical Laboratory
Cascade Tunnels over a range of exit flow Mach numbers . The flow field and heat transfer characteristics of the cascades were also code based on Denton's method and the boundary layer code incorporating K- E turbulence model. The results indicated that there was a scope for improving the blade
profile sections for high Mach number applications
