This is Part Four of a four-part paper. It begins with Section 16.0 and concludes the description of the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, the computational predictions made using several modern boundary layer codes are presented. Both steady codes and an unsteady code were evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate transition and predict loss. Conclusions from the computational analyses are then presented.
Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses
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Halstead, D. E., Wisler, D. C., Okiishi, T. H., Walker, G. J., Hodson, H. P., and Shin, H. (January 1, 1997). "Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses." ASME. J. Turbomach. January 1997; 119(1): 128–139. https://doi.org/10.1115/1.2841001
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