Abstract
In order to improve launching capability and reliability of the H-II rocket, the development of the H-IIA rocket has been under way. High suction performance is required for the H-IIA liquidoxgen turbopump inducer. At the National Aerospace Laboratory, the 64 degree sweepback inducer which was designed for the H-IIA and the 90 degree sweepback inducer which was usedfor the H-II were examined and compared with each other to support its development. From visual observations, cavitation shapes formed at inducer inlet seemed to be effected by sweepback angles.
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