Rocket Nozzle Design Thesis

Preliminary design optimal techniques were adopted to reduce nozzle length while keeping the exit area constant in the design.

Optimization produced a smooth flow by generating a parallel and uniform flow at the exit. in Aeronautical Engineering from Seoul National University in 19, respectively. D from the University of Illinois in Urbana-Champaign in 1992. Lee is currently a Professor at the Department of Aerospace Engineering in Konkuk University in Seoul, Korea.

the trajectory which costs the least amount of propellant.

First some background information as well as the differences between thrust limited and power limited rockets will be discussed.

In this thesis a practical investigation on cryogenic tank pressurization is conducted together with DARE. Methane is a promising propellant for future liquid rocket engines.

In the cooling channels of a regeneratively cooled engine, it would be close to the critical point.

A two-dimensional model was initially used because of the axisymmetrical characteristic of the flow in this study. His research interests are in the area of combustion instabilities of rocket and jet propulsions.

The optimal nozzle was designed for the operation of a test facility at Mach number 2.3 and altitude of 7 km. from Mandalay Technological University (MTU, Myanmar) in 2004 and M. in Mechanical Engineering from Yangon Technological University (YTU, Myanmar) in 2006. D candidate for Aerospace Information Engineering at Konkuk University in Seoul, Korea.

Although many studies have been conducted on nozzle design, none of these present a robust yet practical and simple method for designing supersonic nozzles.

This research attempts to develop such design for supersonic nozzles by combining method of characteristics (MOC), optimization algorithm, and computational fluid dynamics analysis for design verification.


Comments Rocket Nozzle Design Thesis

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