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

Table 3

𝐶₁ values for (17) [55].

Hole configuration	First row	Both rows
Round axial	0.29	0.70
Round compound	4.78	2.71
Round radial	3.93	2.70
Shaped axial	2.10	2.40