The technology could be used for any situation where it is necessary to pump a low vapor pressure fluid. Nuclear reactor boiler feed pumps, vehicle fuel pumps, and cryogenic fluid transfer pumps are all potential commercial applications. In addition, the inducer suction performance predictive capability that will be validated and enhanced during this project will be incorporated into Concepts NREC's suite of commercially available turbomachinery design software tools. The technology could be used as a retrofit onto current, in development, or future rocket engines for launch vehicle or in space propulsion that require high suction performance, high turbopump efficiency, and wide operating range. It is ideally suited for clean sheet engine designs where the full advantage of moving a key system constraint, pump suction performance, can be used to optimize the entire launch system. The technology could also be used for propellant ground handling systems and aircraft fuel pumps were fuel vaporization is an issue. Finally, the code validation work in the technology development will enhance the turbopump design tools used by NASA and improve the suction performance prediction capability.