Post-shock flow in micro-channels: a numerical investigation and analysis

Abstract

Shock propagation at microscales has been an area of utmost interest in recent years due to the recent developments in the fields of micro-electro-mechanical systems (MEMS) and medical science. In the present investigation, post-shock boundary layer flow is numerically examined for shock wave propagation in micro-ducts of 1000 \(\upmu \)m \(\times \) 150 \(\upmu \)m, 1000 \(\upmu \)m \(\times \) 300 \(\upmu \)m, and 1000 \(\upmu \)m \(\times \) 400 \(\upmu \)m cross sections at incident shock Mach numbers ranging from 1.97 to 2.31, similar to the experimental investigations of Giordano et al. (Shock Waves 28:1251–1262, 2018). The shock is introduced using the stagnation properties corresponding to the Mach number of shock-induced flow. The shock position and the shock wave attenuation parameter are compared with the experimental findings of Giordano et al. Numerical results suggest the existence of a turbulent boundary layer behind the shock wave similar to the experimental findings.