716 超音速流中に垂直に噴出する音速噴流と境界層の干渉(OS7-6 航空宇宙推進(流体,燃焼))(OS7 北海道における航空宇宙工学研究の進展と未来)

概要

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A sonic jet was injected into the cross flow from a circular injector, on a flat plate was been putting in supersonic cross flow inclined. The flow field was analyzed by using relation of the penetration of jet height and the jet-to-freestream momentum flux ratio. From the result, it can be known that the penetration height is relying to the momentum flux ratio proportionately by the power of 0.68 and 0.70 in the experiment. And it also can be seen that, for the momentum flux ratio increased, the separated boundary layer region and bow shock scale were increased, when interaction between boundary layer on the flat plate and shock wave formed by the sonic jet was observed and analyzed. Moreover, the penetration height is affected by interaction of the bow shock and boundary layer.
社団法人日本機械学会の論文
2001-09-25