A de Laval supersonic nozzle with a test section was designed as a microsupersonic wind tunnel and subjected to numerical and experimental analysis. The height and depth of the throat of the nozzle were 500 and 150 μm, respectively. A plenum chamber was added to the inlet of the supersonic nozzle and a reservoir was connected to the outlet of the test section to ensure a steady pressure condition during experiments. The microsupersonic wind tunnel was fabricated through microelectromechanical lithography, and a pressure-sensitive paint (PSP) was applied to acquire the pressure contours inside the microsupersonic wind tunnel at various pressure conditions. A divergent angle of 4 deg was added to the test section to resolve the viscous layer growing from the side walls and to ensure a steady flow during the measurements. A flow speed of Mach 1.6 was achieved with inlet and outlet pressures of 100 and 20 kPa, respectively. A circular cylinder model with a diameter of 50 μm was positioned at the exit of the test section to examine the flowfield. Because of the viscous effect, the shock wave cannot be identified but local high- and low-pressure regions could still be observed through PSP measurements.