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.
