Design of Hypersonic Scramjet Engine Operating Between Mach 5 to Mach 9

The Design of Hypersonic Scramjet Engine Operating Between Mach 5 to Mach 9 course provides a deep dive into the principles, design, and performance analysis of air-breathing propulsion systems for hypersonic vehicles. Scramjet engines play a crucial role in next-generation aerospace technologies, enabling high-speed flight for missiles, spaceplanes, and reusable launch systems. This course explores the fundamental concepts of supersonic combustion, shockwave interactions, and stream thrust analysis, equipping learners with the knowledge needed to design and analyze scramjet components such as inlets, isolators, combustors, and nozzles. With a strong emphasis on computational modeling and MATLAB-based simulations, this course bridges the gap between theoretical understanding and practical application in hypersonic propulsion.

Designed for aerospace engineers, CFD specialists, propulsion researchers, and students, this course covers key aerodynamic challenges, including thermal management, Mach number variations, and fuel-air mixing efficiency. Learners will gain hands-on experience in numerical simulations and MATLAB programming, allowing them to evaluate pressure distributions, temperature variations, and combustion stability in scramjet engines. By the end of this course, participants will be equipped with the analytical tools and technical knowledge to contribute to cutting-edge advancements in hypersonic propulsion technology, with applications in defense, space exploration, and high-speed transport systems.

Abstract:

In recent years due to its high performance and efficiency, scramjet engine (also recognized as supersonic combustion ramjet) has gained remarkable significance in the field of hypersonic air-breathing propulsion. The idea behind this research is to develop a rapid design tool for quick estimation of scramjet configuration for hypersonic range of Mach 5 to Mach 9. This paper includes preliminary design of each scramjet component namely; inlet, isolator, combustor and nozzle. Based on the reliability and accuracy of available scramjet thrust estimation methods, stream thrust analysis method is selected for thrust estimation of designed scramjet engine. The paper focuses on establishing a generic MATLAB code which enables the user to design scramjet geometry at various design point conditions which would later be used for a variety of applications including missile propulsion systems and space access missions. The code is developed by integrating design algorithms of each scramjet component and stream thrust analysis. This code enables user to easily determine the configuration and design parameters of the scramjet based on user defined inputs such as altitude, free-stream Mach (between Mach 5 to Mach 9), exit Mach, inlet height and fuel. While, geometry of scramjet and stream thrust calculation results are obtained as output. Lastly, configuration and design parameters of designed scramjet is compared with existing scramjet engines to conclude and verify the results of the MATLAB code.

Link:

10.1109/ICASE48783.2019.9059159