Date of Award
2016
Document Type
Thesis
Degree Name
M.S. in Engineering Science
Department
Mechanical Engineering
First Advisor
Jeffrey A. Roux
Second Advisor
Tejas Pandya
Third Advisor
Erik Hurlen
Relational Format
dissertation/thesis
Abstract
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.
Recommended Citation
Tiruveedula, Lakshmi Srikanth, "Constant Velocity Combustion Scramjet Analysis" (2016). Electronic Theses and Dissertations. 1073.
https://egrove.olemiss.edu/etd/1073
Concentration/Emphasis
Emphasis: Mechanical Engineering