日本航空宇宙学会誌
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
オリフィスのある衡撃波管内の流れ
保原 充野沢 隆二郎飯高 隆滝 史郎
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ジャーナル フリー

1969 年 17 巻 190 号 p. 413-416

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The effect of orifice located in a shock tube is studied experimentally by using pressure probes, and a characteristics method is applied to solve the flow field by taking the experimental orifice condition into account. The orifice condition used is derived from a modified JENNY's formula for the pressure drop, with the additional mass and energy conservation equations. The results show that calculations including the effect of orifice agree with the experimental pressure variation.

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© The Japan Society for Aeronautical and Space Sciences
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