Results 241 to 250 of about 21,342 (292)

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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Physics and Regimes of Supersonic Combustion

AIAA Journal, 2010
Understanding the physics of supersonic combustion is the key to design a performing engine for scramjet-powered vehicles. Despite studies on supersonic combustion dating back to the 1950s, there are still numerous uncertainties and misunderstandings on this topic.
INGENITO, ANTONELLA, Claudio Bruno
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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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Vortex mixing for supersonic combustion

Symposium (International) on Combustion, 1969
Fundamental concepts of mixing and combustion theory are examined in order to define an optimum system. By analogy with the familiar parameter “combustion intensity,” a “mixing intensity” is defined as the total mass of fuel and air mixed per unit time, volume, and density.
J. Swithebank, N.A. Chigier
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Application of Supersonic Combustion to Ramjets

Aircraft Engineering and Aerospace Technology, 1966
THE interest shown lately in ramjet‐type engines for propulsion of hypersonic vehicles within the atmosphere has led us to consider using supersonic combustion ramjets, also called scramjets. It appears that this type of combustion is mandatory when the flight Mach number is of the order of 12.
Louis Viaud, André Mestre
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FUNDAMENTAL ASPECTS OF SUPERSONIC COMBUSTION

1970
Abstract : The application of turbulence theory to the design of supersonic combustors has been investigated both experimentally and theoretically. Experimental studies carried out in the 150 mm shock tunnel have shown that a vortex fuel injector can release the heat extremely rapidly (about 200mm) at a stream velocity of about 3000 m/s.
M. Jaques, J. Swithenbank
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