Numerical analysis and design optimization of supersonic after-burning with strut fuel injectors for scramjet engines

M. J. Candon, H. Ogawa

研究成果: Contribution to journalArticle査読

10 被引用数 (Scopus)

抄録

Scramjets are a class of hypersonic airbreathing engine that offer promise for economical, reliable and high-speed access-to-space and atmospheric transport. The expanding flow in the scramjet nozzle comprises of unburned hydrogen. An after-burning scheme can be used to effectively utilize the remaining hydrogen by supplying additional oxygen into the nozzle, aiming to augment the thrust. This paper presents the results of a single-objective design optimization for a strut fuel injection scheme considering four design variables with the objective of maximizing thrust augmentation. Thrust is found to be augmented significantly owing to a combination of contributions from aerodynamic and combustion effects. Further understanding and physical insights have been gained by performing variance-based global sensitivity analysis, scrutinizing the nozzle flowfields, analyzing the distributions and contributions of the forces acting on the nozzle wall, and examining the combustion efficiency.

本文言語英語
ページ(範囲)281-296
ページ数16
ジャーナルActa Astronautica
147
DOI
出版ステータス出版済み - 6 2018
外部発表はい

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学

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