Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

<table>Normalized total pressure losses in the freestream flow due to trailing edge, oblique shock waves as dependent upon blowing ratio for round cylindrical holes (RCHs) and conical diffused holes (CDHs), for the symmetric airfoil with film cooling [<a href="/journals/ijrm/2012/957421/#B50">54</a>].</table>

International Journal of Rotating Machinery

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Figure 9

Figure 9: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 9 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 