Results 211 to 220 of about 3,707 (264)

A Computational Method for Combustion in Supersonic Flows

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011
A numerical technique to solve two-dimensional reacting ow eld in chemical nonequilibrium is presented. The aim of this study is to develop a computational tool which permits the analysis of combustion phenomena at high speed ows. The numerical approach is based on a time-dependent, nite-volume integration of the Euler equations suitably modi ed for ...
FERRAT, CHRISTIAN, MARSILIO, Roberto
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Discussion on Supersonic Combustion

1992
I work at the University of California. Lore of the sixties was that these engines could not afford normal shocks and yet in very much of your presentation you emphasized perpendicular injection. Is that lore correct?
A. Kumar, M. Y. Hussaini
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Ignition delay in diffusive supersonic combustion

3rd Propulsion Joint Specialist Conference, 1967
This paper deals with the study of the zone located near the injector exit of an idealized supersonic combustion burner using hydrogen as fuel. The ignition delay length is calculated considering a constant-pressure, free mixing layer, where fuel and oxidizer mix without appreciable concentration change or heat release resulting from chemical reactions,
I. DA-RIVA, J. L. URRUTIA
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The simulation of combustion flow of the supersonic combustion chamber

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2011
The phenomenon of supersonic combustion chamber is very complex, full of shock wave system, expansion wave system. It is related to the supersonic, hypersonic flows in the shock/shock intersection, shock wave and boundary layer interaction, separated flow, fuel flow, as well as the complex structure of vortex structures.
Du Ping, Jianhua Chen, Yonghua Tan
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Research on supersonic combustion

30th Aerospace Sciences Meeting and Exhibit, 1992
Introduction S OME qualifications to the pretentious nature of the title of this Paper are in order. Research in this context is applied, i.e., it is directed toward the design and development of devices. The devices are air breathing propulsion systems, wherein supersonic combustion is inherent or it provides an adjunct benefit. Principal applications
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On autoignition-dominated supersonic combustion

45th AIAA Fluid Dynamics Conference, 2015
Supersonic combustion in hydrocarbon-fueled scramjets, in the lower limits of hypersonic flight Mach numbers, is expected to occur as autoignition-dominated distributed reactions. At relevant conditions, including leading to autoignition is not well-captured by detailed chemical-kinetic models at present.
Cymbalist, Niccolo, Dimotakis, Paul
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Combustion in Supersonic Flows and Scramjet Combustion Simulation

2017
The scramjet (supersonic combustion ramjet) is an air-breathing engine with the supersonic flow at the combustor entrance, i.e., with essentially lower deceleration of flow in the inlet with respect to common ramjet. The scramjet is designed for hypersonic flight of vehicle with Mach number large than 5 or 6, where the efficiency of a subsonic ramjet ...
Vladimir A. Sabelnikov, Vladimir V. Vlasenko   +1 more
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The dynamics of unsteady supersonic combustion

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
The dynamic behavior of an unsteady, three-dimensional supersonic flowfield with nonequilibrium chemistry was numerically analyzed. The effects of turbulence were accounted for using the concepts of large eddy simulation (LES) and implemented in an existing threedimensional solver of the compressible Navier-Stokes equations with chemical reactions ...
M. Kallenberg, E. von Lavante
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Flamelet Modeling for Supersonic Combustion

2020
Flamelet models have proven useful in enabling fast and accurate simulations of subsonic turbulent combustion. However, in supersonic combustion, these models face many challenges. The current work presents an a priori analysis of the steady flamelet model using the HIFiRE Direct Connect Rig (HDCR) dual-mode scramjet combustor.
Tomasz G. Drozda, Jesse R. Quinlan, J. Philip Drummond   +2 more
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Supersonic Combustion Technology

1968
The introduction of ballistic missiles as a major element of a modern military strategic offense has abruptly arrested the systematic development of advanced air transportation systems which have been traditionally supported in the initial stages on the basis of military requirements.
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