DocumentCode
526567
Title
Notice of Retraction
Numerical simulation method research for Scramjet Integration Performance
Author
Gong Weijie ; Tang Shuo
Author_Institution
Coll. of Astronaut., Northwestern Polytech. Univ., Xi´an, China
Volume
8
fYear
2010
fDate
9-11 July 2010
Firstpage
265
Lastpage
269
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.
Scramjet technology is one of the key technologies of hypersonic vehicle design powered by air-breathing engine, and its work progress is extremely complicated. In order to explore the scramjet working condition and the operation mechanism, the Scramjet Integration Performance is calculated by Numerical Simulation Method which adopts the two-dimensional NS equation, explicit MacCormack format. The inside flow field of scramjet is analyzed to different mach numbers. And for the complex chemical reactions of the combustor, a hydrogen- oxygen chemical reaction model is created to analyze the baseline model chemical reactions of the combustor, and the reasonable proposals are presented for the baseline model.
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.
Scramjet technology is one of the key technologies of hypersonic vehicle design powered by air-breathing engine, and its work progress is extremely complicated. In order to explore the scramjet working condition and the operation mechanism, the Scramjet Integration Performance is calculated by Numerical Simulation Method which adopts the two-dimensional NS equation, explicit MacCormack format. The inside flow field of scramjet is analyzed to different mach numbers. And for the complex chemical reactions of the combustor, a hydrogen- oxygen chemical reaction model is created to analyze the baseline model chemical reactions of the combustor, and the reasonable proposals are presented for the baseline model.
Keywords
Mach number; aircraft; chemical reactions; jet engines; missiles; numerical analysis; Mach numbers; air-breathing engine; combustor; explicit MacCormack format; hydrogen-oxygen chemical reaction; hypersonic vehicle; numerical simulation; scramjet integration; scramjet technology; two-dimensional NS equation; Analytical models; Atmospheric modeling; Chemicals; Isolators; Numerical Simulation; chemical reaction; hypersonic vehicle; integrated design;
fLanguage
English
Publisher
ieee
Conference_Titel
Computer Science and Information Technology (ICCSIT), 2010 3rd IEEE International Conference on
Conference_Location
Chengdu
Print_ISBN
978-1-4244-5537-9
Type
conf
DOI
10.1109/ICCSIT.2010.5564606
Filename
5564606
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