Accurate simulation of discontinuities induced by detonations

機構典藏 > College of Engineering > Graduate Institute & Department of Aerospace Engineering > Journal Article > Item 987654321/124294

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Title:	Accurate simulation of discontinuities induced by detonations
Authors:	Niu, Yang-yao
Keywords:	Pulse Detonation Engines;Detonation Wave;Shock wave;AUSMD
Date:	2023-06
Issue Date:	2023-07-26 12:05:15 (UTC+8)
Publisher:	Aeronautical and Astronautical Society of the Republic of China
Abstract:	In this study, we propose the HMSTH (Hybrid MUSCL with THINC-EM) [6, 11] type AUSMD [5] flux scheme to solve the stiff Euler equations to achieve an accurate simulation of the detonation waves. When the detonation wave propagates downstream after being ignited in the combustion, it produces a supersonic wave through the nozzle to achieve the thrust cycle called the Pulse Detonation Engine (PDE). [10] The PDE has a great advantage in energy efficiency according to many studies, so its development is important in the future. To overcome the applicant issue making the PDE work smoothly. We work to build an appropriate numerical method. To verify it, one and two-dimensional shock tube problems and the PDE combustion are chosen as the benchmark cases. The numerical results show that the proposed HMSTH-type AUSMD scheme has great potential in simulating further complicated detonation waves and PDE problems.
Relation:	Journal of Aeronautics, Astronautics and Aviation 55(2),　p.119-134
DOI:	10.6125/JoAAA.202306_55(2).02
Appears in Collections:	[Graduate Institute & Department of Aerospace Engineering] Journal Article

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