BOUNDARY-LAYER DEVELOPMENT IN AXIAL COMPRESSORS AND TURBINES .2. COMPRESSORS

This is Part Two of a four-part paper. It begins with Section 6.0 and continues to describe the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer develop ment on airfoil surfaces in multistage turbomachinery. In this part, w e present the experimental evidence used to construct the composite pi cture for compressors given ill the discussion in Section 5.0 of Part 1. We show the data from the surface hot-film gages and the boundary l ayer surveys, give a thorough interpretation Sor the baseline operatin g condition, and then show how this picture changes with variations in Reynolds number, airfoil loading, frequency of occurrence of wakes an d wake turbulence intensity. Detailed flow features are described usin g raw time traces. The use of rods to simulate airfoil wakes is also e valuated.