Abstract
We were success to direct visualize for a rocket engine turbopump inducer with cryogenic fluid (Liquid nitrogen). Tip vortex cavitation was observed from blade tip at cavitation number 0.1. Moreover, both backflow vortex cavitation and sheet cavitation was occurred inlet of the inducer and on the blade surfaces at lower cavitation number. Then, bobble of cavity was miniaturized in comparison with the water tunnel test.
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