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Maximum thrust nozzle based on height constraint
Version 1
: Received: 4 October 2023 / Approved: 5 October 2023 / Online: 5 October 2023 (10:13:20 CEST)
A peer-reviewed article of this Preprint also exists.
Huang, B.; Xu, J.; Yu, K. Maximum-Thrust Nozzle Based on Height Constraints. Aerospace 2023, 10, 976. Huang, B.; Xu, J.; Yu, K. Maximum-Thrust Nozzle Based on Height Constraints. Aerospace 2023, 10, 976.
Abstract
Hypersonic aircraft focuses more on the integration of aircraft and engine than ordinary aircraft owing to high performance requirements, and the nozzle design is reflected in the required large area ratio of nozzle inlet and outlet and the compactness of the overall size of the aircraft. In this study, the height constraint is directly introduced into the maximum thrust nozzle design method. A new method for designing nozzles under the height constraints that consults the maximum thrust theory is proposed. Initially, the condition that the nozzle reaches the maximum thrust under the height constraint is deduced mathematically. Then, a nozzle design method satisfying the height constraint is computed using the method of characteristics (MOC). Subsequently, the influence of the design parameters on the design method is studied parametrically. Results show that Mach number scale and asymmetrical factors can affect ramp length and flap length of the nozzle, respectively. These factors great influence the axial thrust performance and lift under a specific height constraint. Compared with the traditional truncation design method, the thrust coefficient and lift increased by 11.93% and 138.45% respectively.
Keywords
maximum thrust theory; MOC; height constraints; nozzle; scramjet
Subject
Engineering, Aerospace Engineering
Copyright: This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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