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Introduction
Supersonic combustion is a complex phenomena that involves the high-speed mixing of fuel and oxidizer in a supersonic flow regime, leading to extremely high temperatures and pressures. Understanding the fluid dynamics of supersonic combustion is crucial for the development of hypersonic propulsion systems, scramjets, and other high-speed aerospace technologies.
This thesis aims to investigate the fluid dynamics of supersonic combustion, focusing on the interactions between the shock waves, combustion processes, and flow properties. By studying these interactions, we hope to gain insights into the mechanisms governing supersonic combustion and improve the design and performance of hypersonic propulsion systems.
Chapter 1: Introduction
1.1 Introduction
1.2 Background of study
1.3 Problem Statement
1.4 Objective of study
1.5 Limitation of study
1.6 Scope of study
1.7 Significance of study
1.8 Structure of the Thesis
1.9 Definition of terms
Chapter 2: Literature Review
2.1 Historical development of supersonic combustion
2.2 Fundamentals of supersonic flow and combustion
2.3 Previous studies on supersonic combustion
2.4 Shock wave interactions in supersonic combustion
2.5 Combustion processes in supersonic flow
2.6 Flow control techniques in supersonic combustion
2.7 Computational fluid dynamics (CFD) simulations of supersonic combustion
2.8 Experimental techniques for studying supersonic combustion
2.9 Challenges and future directions in supersonic combustion research
2.10 Summary of literature review
Chapter 3: System Design and Methodology
3.1 Design of experimental setup
3.2 Selection of fuels and oxidizers
3.3 Measurement techniques for flow properties
3.4 Numerical modeling approaches
3.5 Calibration and validation of numerical models
3.6 Data acquisition and analysis methods
3.7 Parametric studies and sensitivity analysis
3.8 Optimization techniques for supersonic combustion systems
Chapter 4: System Implementation
4.1 Fabrication of test rig components
4.2 Assembly and integration of experimental setup
4.3 Testing procedures and safety protocols
4.4 Data collection and analysis
4.5 Comparison of experimental results with numerical simulations
4.6 Performance evaluation of supersonic combustion system
4.7 Validation of experimental findings
4.8 Discussion of results
Chapter 5: Conclusion and Summary
5.1 Summary of key findings
5.2 Implications of research results
5.3 Contributions to the field of supersonic combustion
5.4 Recommendations for future research
5.5 Concluding remarks
Thesis Overview:
The thesis on Fluid dynamics of supersonic combustion aims to investigate the complex interactions between shock waves, combustion processes, and flow properties in high-speed supersonic flow regimes. The study is motivated by the growing importance of hypersonic propulsion systems in aerospace technology and the need for a deeper understanding of supersonic combustion phenomena.
The thesis is organized into five chapters, each focusing on a specific aspect of the research. Chapter 1 provides an introduction to the study, outlining the background, problem statement, objectives, scope, limitations, significance, and the structure of the thesis. Chapter 2 reviews the existing literature on supersonic combustion, covering historical developments, fundamental principles, previous studies, challenges, and future directions.
Chapter 3 describes the system design and methodology used in the research, including the experimental setup, selection of fuels and oxidizers, measurement techniques, numerical modeling approaches, data analysis methods, and optimization techniques. Chapter 4 presents the system implementation process, detailing the fabrication of test rig components, assembly of the experimental setup, testing procedures, data collection, analysis, validation, and performance evaluation.
Chapter 5 concludes the thesis by summarizing the key findings, discussing the implications of the research results, highlighting the contributions to the field of supersonic combustion, making recommendations for future research, and providing concluding remarks.
Overall, the thesis aims to advance the understanding of supersonic combustion and contribute to the development of more efficient and reliable hypersonic propulsion systems. By investigating the fluid dynamics of supersonic combustion, we hope to pave the way for innovative solutions in high-speed aerospace technology.
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