Aeronautical and Space Sciences Japan
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
Flow in a Shock Tube with an Orifice
Michiru YASUHARARyujiro NOZAWATakashi IIDAKAShiro TAKI
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1969 Volume 17 Issue 190 Pages 413-416

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Abstract
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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