Design and Optimization of Rocket Engine Nozzle Flow Field Based on Multi-Objective Optimization Algorithm

Morphology optimization is an effective approach for designing rocket engine nozzles, but it can be time-consuming when using high-fidelity models. Therefore, in the early design phase, shape optimization may be possible using simulations that cover a larger design area at a lower accuracy level. In this work, we use a multi-objective optimization method to enhance the flow of rocket engine nozzles with a faster low-fidelity approach. Similar to the proposed approach, high-fidelity simulations are repeated and a Euler solver is utilized within the SU<inf xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">2</inf> open-source framework to assess reliability. The subsequent surrogate-based optimization technique reduces processing power requirements and addresses limitations of doing shape optimization on nozzles within the SU2 framework. Results indicate minimal differences between methodologies for optimal contour width and coefficient of thrust, demonstrating that the developed shape optimization method based on MoC works well for initial nozzle design.