Constant Velocity Combustion Scramjet Analysis

The supersonic combustion ramjet or scramjet, is the most suitable engine cycle for sustained hypersonic flight in the atmosphere. The present work deals with the performance of a scramjet engine by parametrically analyzing the performance of the ideal scramjet using the engine parameters: specific thrust, fuel-to-air ratio, thrust specific fuel consumption, thermal efficiency, propulsive efficiency, overall efficiency and thrust flux. The objective of the work is to determine the desirable performance terms of the ideal scramjet, by varying three different candidate fuels and three different candidate materials for the combustion chamber. The engine parameters are related by the lower heating value (hpr) of the fuel and the maximum service temperature (tmax) of the material. This convenient mathematical equations are development for ideal scramjet performance. The knowledge offered on this work has not been achieved by using others within the scientific literature.

Name thesis:degree_name

M.S. in Engineering Science

Level thesis:degree_level

Thesis

Discipline thesis:degree_discipline

Mechanical Engineering

Year dc:date.available

2016

Author dc:creator

• Tiruveedula, Lakshmi Srikanth

Contributors dc:contributor

• Jeffrey A. Roux
• Tejas Pandya
• Erik Hurlen

• Aerospace Engineering

Repository record dc:identifier

https://egrove.olemiss.edu/etd/1073

OAI identifier oai:identifier

oai:egrove.olemiss.edu:etd-2072