@article{article_1717146, title={A Parametric and Performance-Based CFD Investigation Of The Effect Of Cavity Geometry and Location Of Injector On Flame Stabilization In Supersonic Flow}, journal={International Journal of Energy Horizon (IJEH)}, volume={1}, pages={1–7}, year={2025}, author={Akın, Barış and Alobeid, Mohammad and Kılıç, Ahmed Emin}, keywords={Scramjet Yanması, Boşluk Geometrisi, Yakıt Enjeksiyon Konumu, Alev Stabilizasyonu, CFD Simülasyonu}, abstract={Scramjet (Supersonic Combustion Ramjet) engines are a key propulsion technology for hypersonic flight, where stable combustion and efficient fuel–air mixing under supersonic conditions remain fundamental challenges. This study presents a two-dimensional computational fluid dynamics (CFD) investigation to optimize cavity geometry and fuel injection configurations in a scramjet combustor to enhance mixing and flame stabilization. Rectangular and trapezoidal cavity geometries were assessed under varying hydrogen injection pressures (1, 2, and 3 atm) and locations (top, middle, and bottom) using ANSYS Fluent. A density-based solver incorporating the SST k-ω turbulence model and the Eddy Dissipation Model was employed to simulate reactive flow dynamics. Validation of the numerical model was performed through comparison with experimental data, ensuring mesh independence and agreement on normalized pressure profiles. Results showed that injection location and cavity geometry significantly influence flow recirculation, fuel retention, and temperature distribution. The middle injection at 2 atm in the rectangular cavity yielded the most uniform vortex formation and highest combustion efficiency. In contrast, top injection configurations consistently resulted in poor flame holding due to bypassing of the cavity. For the trapezoidal cavity, middle and bottom injections at 2 atm exhibited comparable mixing behavior, albeit with lower peak temperatures. Overall, the rectangular cavity with centerline injection at 2 atm demonstrated optimal performance for sustained combustion in supersonic flow. These findings contribute to the design of efficient flameholders in scramjet systems, offering insights for improved performance in future hypersonic propulsion applications.}, number={1}, publisher={Ankara Yıldırım Beyazıt Üniversitesi}