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

<table>Comparison of normalized integrated aerodynamic loss magnitudes as dependent upon exit Mach number, and measured one chord length downstream of the cambered and symmetric airfoils, for <svg height="12.0625" id="M258" style="vertical-align:-0.1911pt" version="1.1" viewbox="0 0 93.949997 12.0625" width="93.949997" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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</svg> percent for a cambered vane [<a href="/journals/ijrm/2012/957421/#B49">38</a>].</table>

International Journal of Rotating Machinery

fig19

Figure 19

Figure 19: Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 

Figure 19 | Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number 