ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Insights into the shockwave attenuation in miniature shock tubes

Janardhanraj, S and Abhishek, K and Jagadeesh, G (2021) Insights into the shockwave attenuation in miniature shock tubes. In: Journal of Fluid Mechanics .

jou_flu_mec_2021.pdf - Published Version

Download (2MB) | Preview
Official URL: https://doi.org/10.1017/jfm.2020.914


Miniature shock tubes are finding growing importance in a variety of interdisciplinary applications. There is a lack of experimental data to validate the existing shock tube flow models that explain the shockwave attenuation in pressure-driven miniature shock tubes. This paper gives insights into the shock formation and shock propagation phenomena in miniature shock tubes of 2, 6 and 10 mm square cross-sections operated at diaphragm rupture pressure ratios in the range 5-25 and driven section initially at ambient conditions. Pressure measurements and visualization studies are carried out in a new miniature table-top shock tube system using nitrogen and helium as driver gases. The experimental findings are validated using a shock tube model explained in terms of two regions: (i) the shock formation region, dominated by wave interactions due to the diaphragm's finite rupture time; and (ii) the shock propagation region, where the shockwave attenuation occurs mainly due to wall effects and boundary layer growth. Correlations to predict the variation of shock Mach number in the shock formation region and shock propagation region work well for the present findings and experimental data reported in the literature. Similar flow features are observed in the shock tubes at the same dimensionless time stamps. The formation of the planar shock front scales proportionally with the diameter of the shock tube. The peak Mach number attained by the shockwave is higher as the shock tube diameter increases.

Item Type: Journal Article
Publication: Journal of Fluid Mechanics
Publisher: Cambridge University Press
Additional Information: The copyright for this article belongs to the Authors.
Keywords: Acoustic wave propagation; Aerodynamics; Boundary layers; Mach number; Tubes (components), Ambient conditions; Boundary layer growth; Pressure ratio; Pressure-driven; Shock formation; Shock propagation; Square cross section; Wave interactions, Shock tubes
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 05 Jun 2023 07:11
Last Modified: 05 Jun 2023 07:11
URI: https://eprints.iisc.ac.in/id/eprint/81757

Actions (login required)

View Item View Item