DocumentCode
518299
Title
Notice of Retraction
Drag force characteristic of a typical dual-mode scramjet combustor
Author
Shi-bin Luo ; Wei Huang ; Jing Lei ; Jun Liu ; Zhen-guo Wang
Author_Institution
Center of Hypersonic Propulsion, Nat. Univ. of Defense Technol., Changsha, China
Volume
5
fYear
2010
fDate
16-18 April 2010
Abstract
Notice of Retraction
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
The two-dimensional dimensional coupled implicit NS equations, the standard k-ε turbulent model and the Finite-Rate/Eddy-Dissipation reaction model were used to numerical simulate the flowfiled of the dual-mode scramjet combustor, including the engine ignited condition and the cold flow condition. At the same time, the influence of the injection modes, namely transversely and horizontally, on the drag force characteristic of the combustor was investigated. The obtained results show that the higher injection pressure can promote the mixing process between the fuel and the air stream, and the cases with the higher injection pressure can provide larger thrust. If the hydrogen is injected into the core flow transversely, it can penetrate deeper, and it can also generate larger thrust. So the two methods can be used to reduce the drag force of the combustor in the experimental test.
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
The two-dimensional dimensional coupled implicit NS equations, the standard k-ε turbulent model and the Finite-Rate/Eddy-Dissipation reaction model were used to numerical simulate the flowfiled of the dual-mode scramjet combustor, including the engine ignited condition and the cold flow condition. At the same time, the influence of the injection modes, namely transversely and horizontally, on the drag force characteristic of the combustor was investigated. The obtained results show that the higher injection pressure can promote the mixing process between the fuel and the air stream, and the cases with the higher injection pressure can provide larger thrust. If the hydrogen is injected into the core flow transversely, it can penetrate deeper, and it can also generate larger thrust. So the two methods can be used to reduce the drag force of the combustor in the experimental test.
Keywords
Navier-Stokes equations; combustion equipment; drag reduction; flow simulation; jet engines; two-phase flow; Navier-Stokes equation; cold flow condition; core flow transversal; drag force reduction; dual-mode scramjet combustor; engine ignition condition; finite rate eddy-dissipation reaction model; flowfield simulation; fuel-air stream mixing process; injection pressure; standard k-ε turbulent model; Aerospace materials; Combustion; Drag; Engines; Equations; Fuels; Hydrogen; Propulsion; Temperature; Vehicles; aerospace propulsion system; drag force; hypersonic vehicle; the hydrogen fueled dual-mode scramjet combustor;
fLanguage
English
Publisher
ieee
Conference_Titel
Computer Engineering and Technology (ICCET), 2010 2nd International Conference on
Conference_Location
Chengdu
Print_ISBN
978-1-4244-6347-3
Type
conf
DOI
10.1109/ICCET.2010.5485998
Filename
5485998
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