Author(s)

L.J. Lenke, A.W. Reichert & H. Simon

Abstract

The aerodynamic design of turbomachinery components is a field of economic importance where Computational Fluid Dynamics methods are applied for many years. For the high Mach numbers and the high Reynolds numbers appearing in the components, the accuracy requirements concerning the pre- dicted data are very high. Data of interest are the flow field losses, the flow direction and the shock configuration in supersonic regions. For selected examples from the wide field of turbomachinery design comparisons of nu- merical and experimental results are given for these data. The numerical results are calculated by a State Difference Splitting code of high

Keywords