Mixing and combustion in supersonic/hypersonic flows
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Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: [email protected]
Editorial:
Mixing and combustion in supersonic/hypersonic flows Wei HUANG, Guest Editor-in-Chief Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
Jun-tao CHANG, Guest Editor School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Li YAN, Guest Editor Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China
E-mail: [email protected]; [email protected]; [email protected]
In this special issue, we invited primary scientists on the leading edge in this field and with recent high impact research to share their expertise and perspectives. The collected papers cover various topics, such as shock wave/turbulence boundary layer interaction control, mixing, ignition, and flame stabilization in scramjet combustors, and mode transition in rotating detonation engines.
https://doi.org/10.1631/jzus.A20MCSF1
Under the guidance of the major two-period research program of the National Natural Science Foundation of China, the hypersonic technique has steadily matured. Further development of its core component—the airbreathing hypersonic propulsion system, and of some novel concepts of the combined cycle engine, is needed urgently to meet the power requirements of single/two-stage-to-orbit manned spacecraft and hypersonic aircraft, such as the SR-72 (Fig. 1). However, the resident time of the high-speed flow in the scramjet combustor is very limited, only a few milliseconds, and the generation of useful thrust through additional heat at such high speeds is still a challenging task (Huang et al., 2019). Therefore, many mixing augmentation devices have been proposed and investigated, as well as flame propagation and stabilization mechanisms in the supersonic or hypersonic flow (Huang et al., 2018). Fig. 2 shows the operational process in an airbreathing hypersonic propulsion system. The developed computational fluid dynamics (CFD) approaches, such as the efficient WENOCU4 developed by Li et al. (2020), have contributed greatly to ground experimental testing, especially of approaches with high-order accuracy. ORCID: Wei HUANG, https://orcid.org/0000-0001-9805-985X © Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2020
Fig. 1 SR-72
Schematic diagram of the hypersonic aircraft
Shock wave/boundary layer interaction is a common phenomenon which occurs in the internal and external flow fields of hypersonic vehicles. Zhang et al. (2020) evaluated numerically the influences of the bleed hole diameter, depth, and boundary layer thickness on the bleed mass flow rate of a porous array bleed system in a hypersonic inlet, and explored its potential physical mechanism. Hou et al. (2020) investigated self-excited oscillation in an isolator with background waves
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