Results 241 to 250 of about 301,896 (292)

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
openaire   +2 more sources

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
openaire   +1 more source

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
openaire   +1 more source

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
openaire   +1 more source

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
openaire   +2 more sources

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
openaire   +1 more source

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
openaire   +1 more source

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.
openaire   +1 more source

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
openaire   +1 more source

Combustion Efficiencies of Supersonic Flames

Journal of Propulsion and Power, 2001
Measuredvaluesofcombustionefe ciencyc,whichquantifytheamountofhydrogenfuelthatremainsunburned because the fuel has insufe cient residence time in the reaction zone of a supersonic e ame, are reported. Trends are reported as the fuel e ow rate and the stagnation temperature are systematically varied.
Albert Ratner, James F. Driscoll, Hwanil Huh, Rodney A. Bryant   +3 more
openaire   +1 more source