Nozzle Design for the Supersonic Wind Tunnel Ramjet Attachment

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Carter, Andrew Michael
Ramjet; Nozzle; Engine; Air-Breathing; Converging-Diverging; Propulsion and Power
article description
This document outlines the concept, design, and manufacturing stages of the nozzle section to the Ramjet Attachment. This project is a subsidiary of the thesis, Baseline Performance of Ramjet Engine”, developed by Harrison Sykes. The nozzle geometry is based off of theoretical calculations using Isentropic and Rayleigh line flow relations for a two-dimensional cross section. The nozzle sees an inlet temperature of 953 degrees Fahrenheit, pressure of 28 psi, and a Mach number of 0.356 after the combustion chamber. The nozzle section is a two foot long converging diverging nozzle to choke and accelerate the flow to achieve an exit temperature of 597 degrees Fahrenheit, a pressure of 8.8 psi and a Mach number of 1.5. The thrust of the system is 139 pounds. The nozzle is made out of flat stainless steel type 304 plates jointed together to allow for variable change in the throat and exit areas to choke the flow and optimize performance.