2D Scramjet inlet design and investigation with computational fluid dynamics and sudden expansion tube experiments

Date

2023-4-17

Author

Yanık, Yiğitcan

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A 2D scramjet inlet is designed in this study specifically for operation at Mach 6 and 30 km altitude. The inlet design process is based on 1D performance estimations and included considerations for flow stability, shock wave patterns, and pressure recovery. The performance of the designed inlet is assessed using 2D and 3D CFD simulations and sudden expansion tube experiments at the TÜBİTAK SAGE facility. It is found that the performance of the designed inlet is in good agreement with the 1D estimations at the design point, indicating that the inlet is feasible for operation under these conditions. Similar trends in pressure recovery and shock wave patterns are revealed by both the CFD simulations and sudden expansion tube experiments, with minor differences in the details of the flow field being observed. This study provides insight into the design and performance of 2D scramjet inlets for operation at Mach 6 and 30 km altitude. Further work is needed to optimize the inlet design and study its performance under a wider range of conditions.

Subject Keywords

Scramjet Inlet, Hypersonic Flow, Computational Fluid Dynamics, Sudden Expansion Tube

URI

https://hdl.handle.net/11511/103093

Collections

Graduate School of Natural and Applied Sciences, Thesis