Flow Field behind a Shock Wave in a Low-Pressure Test Gas

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Abstract
A study is made of the two‐dimensional flow field resulting from boundary‐layer growth in the driven gas of a shock tube. Attention is given to circular as well as to rectangular shock tubes. Formulas that describe the axial and transverse velocity components near the shock front are developed and are evaluated numerically. The properties of the two‐dimensional flow field are discussed. It is found that the flow is nearly one‐dimensional at distances greater than a tube radius from the shock front. In the region near the shock front, averaging of the perturbations gives results identical to those of Mirels' quasi‐one‐dimensional theory. An approximate description of the entire flow field can be obtained by taking the average velocity provided by Mirels' theory, and by superimposing the two‐dimensional flow pattern stretched axially so as to conform to the prescribed average. The details of the flow field provided in the present paper can, therefore, be considered a complement to Mirels' work.

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