@article{4cef6619d513490789b71cdfc453083d,
title = "Physical insight into fuel/air mixing with hypermixer injectors for scramjet engines",
abstract = "Efficient mixing of fuel and air is a major objective for the successful operation of scramjet engines, in which the supersonic combustion process must occur within an extremely short time frame in the hypersonic flight. This paper presents the insights gained into the key design factors and underlying mechanism for fuel/air mixing enhancement with streamwise vortices introduced by alternating wedges called hypermixers. The results of a parametric numerical study and sensitivity analysis suggest that narrow spanwise intervals between the alternating wedges and large fuel/air equivalence ratios are beneficial for effective mixing, while higher total pressure recovery is associated with shallower ramp angles and lower fuel/air equivalence ratios. Higher fuel penetration is achieved with steeper ramp angles and higher fuel/air equivalence ratios. Streamwise vortex circulation increases with wider spanwise spacing and steeper ramp angles, but effective mixing enhancement is observed only in the latter case.",
author = "Hideaki Ogawa and Masatoshi Kodera",
note = "Funding Information: The authors wish to acknowledge the support of the Australian Research Council through the Discovery Early Career Researcher Award grant number DE120102277 for H. Ogawa. They are grateful to R. R. Boyce for providing resources in this research project during the appointments at the Centre for Hypersonics, The University of Queensland, as well as to Multidisciplinary Design Optimization Research Group led by Tapabrata Ray at The University of New South Wales Canberra for the capability of surrogate modeling used in the present study. They are also thankful to T. Sunami at Japan Aerospace Exploration Agency Kakuda Space Center for his invaluable advice. They. They also acknowledge the use of the Japan Aerospace Exploration Agency Supercomputer System, on which the numerical simulations presented in this paper were performed. Publisher Copyright: {\textcopyright} Copyright 2015 by the American Institute of Aeronautics and Astronautics, Inc.",
year = "2015",
doi = "10.2514/1.B35638",
language = "English",
volume = "38",
pages = "1423--1435",
journal = "Journal of Propulsion and Power",
issn = "0748-4658",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",
number = "6",
}