Design and Optimization of a Modular Supersonic Blow-Down Wind Tunnel

Designing a supersonic blow-down wind tunnel generally aims to achieve precise and stable flow con ditions over a range of reference Mach numbers and simulated altitudes. A key objective of this study is to investigate the feasibility of a modular wind tunnel configuration capable of adapting to various testing requirements. To achieve this, three nozzles for Mach 2.5, 3.5, and 4.5 have been designed and analyzed using the method of characteristics combined with boundary layer correction. This approach ensures opti mized nozzle contours that minimize flow non-uniformities and boundary layer growth, thereby enhancing the overall flow quality in the test section. In addition to nozzle design, different test section configurations, including both straight and enlarged geometries, are investigated, to assess their effects on flow uniformity, pressure distribution, and measurement accuracy. The influence of these configurations on the develop ment of the boundary layer and shock/boundary layer interactions within the test section is analyzed to identify the optimal configuration for various experimental applications. To ensure a robust and flexible wind tunnel design, both analytical methods and computational fluid dynamics simulations are employed, allowing for a comprehensive evaluation of key parameters such as tunnel geometry, flow stability, and boundary layer control. The final design aims to provide a modular and reliable testing environment with steady and accurate flow characteristics sustained over extended test durations