Parametric Scramjet Analysis

The performance of a hypersonic flight vehicle will depend on existing materials and fuels; this work presents the performance of the ideal scramjet engine for three different combustion chamber materials and three different candidate fuels. Engine performance is explored by parametric cycle analysis for the ideal scramjet as a function of material maximum service temperature and the lower heating value of jet engine fuels. The thermodynamic analysis is based on the Brayton cycle as similarly employed in describing the performance of the ramjet, turbojet, and fanjet ideal engines. The objective of this work is to explore material operating temperatures and fuel possibilities for the combustion chamber of a scramjet propulsion system to show how they relate to scramjet performance and the seven scramjet engine parameters: specific thrust, fuel-to-air ratio, thrust-specific fuel consumption, thermal efficiency, propulsive efficiency, overall efficiency, and thrust flux. The information presented in this work has not been done by others in the scientific literature. This work yields simple algebraic equations for scramjet performance which are similar to that of the ideal ramjet, ideal turbojet and ideal turbofan engines.

Name thesis:degree_name

M.S. in Engineering Science

Level thesis:degree_level

Thesis

Discipline thesis:degree_discipline

Mechanical Engineering

Year dc:date.available

2014

Author dc:creator

• Choi, Jongseong

Contributors dc:contributor

• Jeffrey A. Roux

• Efficiency
• Heat Transfer
• Mass Flow Rate
• Parametric
• Ramjet
• Scramjet
• Aerospace Engineering

Repository record dc:identifier

https://egrove.olemiss.edu/etd/535

OAI identifier oai:identifier

oai:egrove.olemiss.edu:etd-1534