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

M. J. Candon, H. Ogawa

Research output: Contribution to journalArticlepeer-review

8 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)281-296
Number of pages16
JournalActa Astronautica
Volume147
DOIs
Publication statusPublished - Jun 2018
Externally publishedYes

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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