Study on Correlation between Geometrical Correction and Aerodynamic Performance of Microscale Supersonic Wind Tunnel

Abstract

In this paper, flow visualization of the oblique shock waves of a single-crystal-silicon microscale supersonic wind tunnel is described. The microscale supersonic wind tunnel has a convergent - divergent section and a throat area of 1000µm×300µm, and designed for realizing supersonic flow of Mach 2 in microscale domain. The schlieren system with integrated optical microscope was used for visualization of the oblique shock waves generated in the microscale domain. To investigate the effect of nonisentropic flow state on the inclination angle to the shock, a numerical integration of the modified Shapiro's differential equation was applied.