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<p>Shock tubes have been widely used to obtain a uniform flow and/or a gas with high pressure and high temperature for aerodynamic, chemical, and combustion studies. Under the ideal condition, the flow properties, such as pressure and temperature, are kept constant during the test time, but in the real world, this may not happen due to the viscous effect, such as the boundary layer development, which depends on the unit Reynolds number. To investigate the effect of the unit Reynolds number on the pressure growth at the end-wall during the test time, experiments were conducted under a range of unit Reynolds numbers from <InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(1.7\times 10^{\textrm{6}}\)</EquationSource> <EquationSource Format="MATHML"><math> <mrow> <mn>1.7</mn> <mo>×</mo> <msup> <mn>10</mn> <mtext>6</mtext> </msup> </mrow> </math></EquationSource> </InlineEquation> to <InlineEquation ID="IEq2"> <EquationSource Format="TEX">\(8.1 \times 10^{\textrm{6}}\)</EquationSource> <EquationSource Format="MATHML"><math> <mrow> <mn>8.1</mn> <mo>×</mo> <msup> <mn>10</mn> <mtext>6</mtext> </msup> </mrow> </math></EquationSource> </InlineEquation> 1/m at the incident shock Mach numbers from 2.0 to 2.3. The schlieren visualization showed that the Shock-Wave/Boundary-Layer Interaction (SWBLI) occurred in the test section and that the structure under bifurcated shock waves varied with the unit Reynolds number. The pressure growth was observed for all the test conditions conducted, and the growth rate of pressure was also varied with both the unit Reynolds number and the incident shock Mach number. The growth rate of pressure at the end-wall decreased from 34 to 9.3 %/ms as the unit Reynolds number increased and the incident shock Mach number decreased.</p>

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Experimental investigation of the effect of unit Reynolds number on unsteady pressure growth behind the reflected shock wave in a shock tube

  • 期刊论文

  • 发表日期：

    2026年3月29日

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  • K. Yoshikawa,
  • A. T. Bicak,
  • H. Ozawa

摘要

Shock tubes have been widely used to obtain a uniform flow and/or a gas with high pressure and high temperature for aerodynamic, chemical, and combustion studies. Under the ideal condition, the flow properties, such as pressure and temperature, are kept constant during the test time, but in the real world, this may not happen due to the viscous effect, such as the boundary layer development, which depends on the unit Reynolds number. To investigate the effect of the unit Reynolds number on the pressure growth at the end-wall during the test time, experiments were conducted under a range of unit Reynolds numbers from \(1.7\times 10^{\textrm{6}}\) 1.7 × 10 6 to \(8.1 \times 10^{\textrm{6}}\) 8.1 × 10 6 1/m at the incident shock Mach numbers from 2.0 to 2.3. The schlieren visualization showed that the Shock-Wave/Boundary-Layer Interaction (SWBLI) occurred in the test section and that the structure under bifurcated shock waves varied with the unit Reynolds number. The pressure growth was observed for all the test conditions conducted, and the growth rate of pressure was also varied with both the unit Reynolds number and the incident shock Mach number. The growth rate of pressure at the end-wall decreased from 34 to 9.3 %/ms as the unit Reynolds number increased and the incident shock Mach number decreased.