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

<table>Comparison of integrated aerodynamic losses as dependent upon Mach number ratio from round cylindrical holes (RCHs) and conical diffused holes (CDH), after correction for the presence of trailing edge oblique shock waves, 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 10

Figure 10: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 10 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 