Computational Analysis Of Shock Tube

Abstract: In this present paper, a computational study is carried out on shock tube to produce a supersonic Mach number. The present work is an effort to simulate a shock wave for studying the response of different materials. The shock tube is widely used for high strain rate testing in many engineering and industrial applications. As the experimental tests on shock tube are time consuming and lot of material is consumed hence using computational based numerical simulation which is helpful in reducing time, effort and cost. This intends to make prediction of wave propagation easy and minimizes the need of experimental testing. Compared to experimental shock tube the simulated shock tube can be helpful to predict the pressure contours and pressure-time graph. In this research paper, simulation study was conducted on a computational shock tube which behaves as that of actual shock tube setup. Using boundary conditions actual shock tube environment is reproduced in the simulation setup. The pressure values obtained during experiment has been patched in ANSYS CFD module. The best effort for solver setup, turbulence models comparison and meshing variation has been done for more accuracy. Overall, simulation method used for current study are able to validate the results of the experimental data accurately for pressure values generated in driver and driven section of shock tube. From the result, we obtain the velocity value which has to be further used in formula to obtain the Mach number. Substitute this value in Mach number formula and then the supersonic Mach number is obtained. Using this analysis hypersonic Mach number can also be sometimes obtained.

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