Combustion Optimization of a Scramjet – A Numerical Flow Investigation Approach

The Scramjet (Supersonic Combustion Ramjet) engine stands at the forefront of next-generation hypersonic propulsion systems, offering exceptional performance by sustaining combustion at supersonic speeds. However, achieving stable, efficient, and complete combustion within the extremely short residence time of high-speed airflow remains one of the most critical and challenging aspects in scramjet development. This study focuses on the optimization of combustion within scramjet engines to enhance overall efficiency, thrust output, and operational stability under hypersonic flight conditions. The primary objective of this project is to investigate and improve the combustion process by examining key influencing parameters such as pressure and velocity. Various computational and theoretical analyses are employed to simulate and study the effects of these parameters on combustion efficiency and stability. Computational Fluid Dynamics (CFD) simulations are conducted to visualize the supersonic flow behaviour, pressure variation, velocity variation and species concentration within the combustion chamber. The study concludes with optimized design recommendations that significantly improve combustion efficiency, reduce total pressure loss, and support high specific impulse generation. These findings not only contribute to better scramjet performance but also pave the way for further research in scramjet-integrated hypersonic platforms for military, space, and commercial applications. Overall, this project contributes to the growing body of knowledge aimed at overcoming combustion challenges in scramjet engines and accelerating the development of reliable and reusable hypersonic propulsion systems.