1. One of the basic, nevertheless very important, design feature is the accurate prediction of airfoil loading. The computed static pressure distributions, non-dimensionalized with the mid span inlet total pressure value, are presented at three different radial locations in figures 6-8. The experimental values obtained from reference 16 are also plotted on these figures. The numerical predictions are in excellent agreement with the data.
2. Computation of Shocked Flows in Compressor Cascades