Combustion of hydrogen injected into a supersonic airstream (the ship computer program) PDF Download
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Author: N. C. Markatos
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 130
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Book Description
Author: N. C. Markatos
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 130
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Book Description
Author: David F. Dyer
Publisher:
ISBN:
Category : Combustion research
Languages : en
Pages : 84
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Book Description
Author: N. C. Markatos
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
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Book Description
Author: R. Clayton Rogers
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Book Description
Author: R. Clayton Rogers
Publisher:
ISBN:
Category : Hydrogen as fuel
Languages : en
Pages : 60
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Book Description
Jet to free-stream dynamic pressure ratio effects on penetration and mixing of hydrogen injected normal to supersonic airstreams.
Author: Malcolm Thomas Jacques
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
The report is concerned with the mixing and combustion of hydrogen in a high enthalpy Mach 3.5 airstream, in which the conditions are such that the combustion process is mixing limited. The high enthalpy conditions are obtained using a combustion driven hypersonic shock tunnel. A gas composition probe having a response time of 0.25 msec. has been constructed and used in contamination and combustion studies. Combustion results have been obtained from a 2-D Mach 3.5 test section using both a mid-stream vortex generating injector and a plain wedge injector. The turbulent mixing characteristics of the two wakes were determined using a semi-quantitative approach which utilizes well established relationships of structural turbulence theory. The results of this analysis showed the importance of the initial turbulence generation on the overall mixing process. (Author).
Author: Malcolm Thomas Jacques
Publisher:
ISBN:
Category :
Languages : en
Pages : 190
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Book Description
The report is concerned with the mixing and combustion of hydrogen in a high enthalpy Mach 3.5 airstream, in which the conditions are such that the combustion process is mixing limited. The high enthalpy conditions are obtained using a combustion driven hypersonic shock tunnel. A gas composition probe having a response time of 0.25 msec. has been constructed and used in contamination and combustion studies. Combustion results have been obtained from a 2-D Mach 3.5 test section using both a mid-stream vortex generating injector and a plain wedge injector. The turbulent mixing characteristics of the two wakes were determined using a semi-quantitative approach which utilizes well established relationships of structural turbulence theory. The results of this analysis showed the importance of the initial turbulence generation on the overall mixing process. (Author).
Author: R. Clayton Rogers
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
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Book Description
Author: K. Uenishi
Publisher:
ISBN:
Category :
Languages : en
Pages : 15
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Book Description
Author: Gautam Choubey
Publisher: Butterworth-Heinemann
ISBN: 0323995667
Category : Technology & Engineering
Languages : en
Pages : 198
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Book Description
Scramjet Combustion explores the development of a high-speed scramjet engine operating in the supersonic/hypersonic range for various air and space transport applications. The book explains the basic structure, components, working cycle, and the relevant governing equations in a clear manner that speaks to both advanced and more novice audiences. Particular attention is paid to efficient air–fuel combustion, looking at both the underlying fundamentals of combustion as well strategies for obtaining optimum combustion efficiency. Methods for reaching the chemically correct air–fuel ratio, subsequent flame, and combustion stabilization as air enters at supersonic speed are also outlined. Further, it includes the continuous on-going efforts, innovations, and advances with respect to the design modification of scramjet combustors, as well as different strategies of fuel injections for obtaining augmented performance while highlighting the current and future challenges. Outlines the fundamentals of scramjet engines including their basic structure and components, working cycle, governing equations, and combustion fundamentals affecting the combustion and mixing processes Presents new design modifications of scramjet combustors and different fuel injection strategies including combined fuel injection approaches Discusses core topics such as chemical kinetics in supersonic flow, fuel–air mixing methods, strategies for combating combustion difficulties, and subsequent flame and combustion stabilization that can be applied to scramjets Describes the pedagogy for computational approaches in simulating supersonic flows
