Benchmarking of Computational Models against Experimental Data for Velocity Profile Effects on CFD Analysis of Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays

This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for full coverage geometries composed of cylindrical staggered holes at a compounded angle of 45 degrees. These holes had an inclination angle of 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. The goal of this research was to test the effects of utilizing a realistic vs a uniform velocity profile at the crossflow inlet and find any significant differences in the results produced when compared to experimental data. The results displayed differences between the spanwise average adiabatic effectiveness for both the uniform velocity profile case and the velocity profile replication of the experimental data when using the Realizable k-ε turbulence model. These differences were found to be due to the differences in the thermal boundary layer predicted by the turbulence model for the two test cases