Supersonic Multi-Objective Optimization of a Rocket Based Combined Cycle Inlet by Differential Evolution

It appears your Web browser is not configured to display PDF files. Download adobe Acrobat or click here to download the PDF file.

Click here to download the PDF file.

Creator: 

Jee, Craig J. L.

Date: 

2018

Abstract: 

The use of differential evolution is investigated for the optimization of a novel rocket based combined cycle (RBCC) engine inlet, over the supersonic flight regime. This novel inlet design, referred to as the exchange inlet, is designed to entrain air using a semi-annular rocket-ejector exhaust profile. In supersonic flight, the exchange inlet external geometry generates shock waves which affect both the air mass flow and total pressure recovery of the entrained air. By treating each unique exchange inlet geometry as an individual in a population, the DE algorithm can narrow in on potential optimal designs using a process similar to natural selection. A single optimum is selected for three flight conditions M=1.5, 2.5 and 3.5. By comparing their off-design performance over the supersonic flight range each geometry is compared to determine an optimal for a fixed geometry design. The fixed geometry design is selected as the optimum at M=2.5.

Subject: 

Engineering - Aerospace
Engineering - Mechanical

Language: 

English

Publisher: 

Carleton University

Thesis Degree Name: 

Master of Applied Science: 
M.App.Sc.

Thesis Degree Level: 

Master's

Thesis Degree Discipline: 

Engineering, Aerospace

Parent Collection: 

Theses and Dissertations

Items in CURVE are protected by copyright, with all rights reserved, unless otherwise indicated. They are made available with permission from the author(s).