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

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  • 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.

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  • Copyright © 2018 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
Date Created
  • 2018


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