Abstract
Development of Computational Fluid Dynamics (CFD) computer codes for complex turbomachinery affords a complete three-dimensional (3-D) flow field description. While significant improvements in CFD have been made due to improvements in computers, numerical algorithms, and physical modeling, a limited experimental database for pump CFD code validation exists.Under contract (NAS8-38864) to the National Aeronautics and Space Administration (NASA) at Marshall Space Flight Center (MSFC) a test program was undertaken at Rocketdyne to obtain benchmark data for typical rocket engine pump geometry. Nonintrusive velocity data were obtained with a laser two-focus velocimeter. Extensive laser surveys at the inlet and discharge of a Rocketdyne-designed impeller were performed. Static pressures were measured at key locations to provide boundary conditions for CFD code validation.