AM05-11-002 ブローダウン流路による翼周りの低温キャビテーション流の可視化(高速液体噴流,キャビテーション,一般講演)

概要

論文の詳細を見る
Cavitation is one of the major problems in the development of cryogenic rocket engines. There have been few experimental studies to visualize cryogenic cavitation around a foil. Therefore a new cryogenic cavitation tunnel of blowdown type was built. The foil shape is "plano-convex". This profile was chosen because of simplicity, but also of being similar to the one for a rocket inducer impeller. Working fluids were water at room temperature, hot water and liquid nitrogen. In case of AOA=8 degree, periodical cavity departure was observed in the experiments of both water at 90degC and nitrogen at -190degC under the same velocity 10m/sec and the same cavitation number 0.7. The frequencies were observed to be 110 and 90Hz, respectively, and almost coincided with those of vortex shedding from the foil. Temperature depression due to the thermodynamic effect was confirmed in experiment especially in the cryogenic cavitation.
日本流体力学会の論文
2005-09-05