Modeling Analysis of Mach Number, Static Pressure, and Static Temperature Distribution In A Supersonic Wind Tunnel

Supersonic wind tunnels are critical tools in aerospace engineering, enabling the study of high-speed aerodynamic phenomena essential for the design and optimization of aircraft and spacecraft. This study employs Computational Fluid Dynamics (CFD) using ANSYS CFX to analyze the distribution of Mach number, static pressure, and static temperature in a supersonic wind tunnel under on-design (Mach 2.0) and off-design (Mach 1.8 and 2.2) conditions. Results indicate that on-design conditions yield stable and uniform flow distributions, while off-design conditions lead to significant instabilities, including shock wave interactions and thermal gradients. These findings emphasize the importance of precise operational configurations for achieving reliable experimental results. The research contributes to the optimization of wind tunnel designs and provides a foundation for future studies involving three-dimensional modeling, experimental validation, and advanced nozzle geometries to enhance the accuracy and applicability of supersonic wind tunnel analyses.