Invention relates to equipment for aerodynamic studies, especially to the supersonic wind tunnel. The inlet nozzle of the supersonic wind tunnel consists of four major components, i.e., settling chamber (1), convergent section (2), divergent section (3), and test section (4).
The purpose of the invention is to ensure the airflow of the supersonic wind tunnel from the settling chamber (1) to the sonic throat (between (2) and (3)) with as minimum as possible turbulence and with a shorter geometry. The divergent section (3) of the inlet nozzle of the developing supersonic wind tunnel was designed with a modified version of the Method of Characteristic (MOC). In the invention, the convergent section (2) of the inlet nozzle connects the settling chamber (1) to the divergent section (3) of the inlet nozzle. This convergent section (2) of the inlet nozzle comprises an asymmetric double arc to ensure the smooth flow transition and acceleration within the convergent section (2) of the inlet nozzle by using different Mach numbers. Moreover, the two-phase geometric morphing design will reduce the manufacturing cost of the supersonic wind tunnel and this design can easily be adapted to any other variants of the wind tunnel.