Results 231 to 240 of about 21,342 (292)

Supersonic Combustion: Modelling and Simulations

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, 2006
Mixing and combustion of supersonic reacting flows are currently under investigation for new generation launchers and trans-atmospheric vehicles. Experimental results with hydrogen injected at Mach 2.5 in a Mach 2 airstreams showed combustion taking place just in ∼0.6 m: this indicates that supersonic combustion is very efficient.
INGENITO, ANTONELLA, C. Bruno, E. Giacomazzi, J. Steelant   +3 more
openaire   +2 more sources

Reaction Regimes in Supersonic Combustion

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, 2009
Large-eddy simulations (LES) of supersonic combustion are considered to be an important tool to better understand the physics of supersonic reactive flows. To correctly predict the flame anchoring and the flame structure, the implementation of a appropriate SGS scale model is crucial, and its physics and derivation are analyzed in the present work.
INGENITO, ANTONELLA, C. Bruno
openaire   +2 more sources

On supersonic combustion

Science in China Series A: Mathematics, 1999
Some basic concepts and features of supersonic combustion are explained from the view point of macroscopic aerodynamics. Two kinds of interpretations of supersonic combustion are proposed. The difference between supersonic combustion and subsonic combustion is discussed, and the mechanism of supersonic combustion propagation and the limitation of heat ...
openaire   +1 more source

Combustion in supersonic flow

Combustion, Explosion and Shock Waves, 1987
Examples of numeric modeling of complex combustion processes in supersonic flows are presented which illustrate the possibility of obtaining useful information which may reveal their basic regularities determined by the parameters of the entrance streams, mode of injection, type of fuel, and the interaction of various factors pertaining to combustion ...
V. K. Baev, V. I. Golovichev, P. K. Tret'yakov   +2 more
openaire   +1 more source

Mixing and Combustion in Supersonic Reactive Flows

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008
Supersonic combustion is a key issue in any future plan to develop supersonic combustion (SC) ramjets (SCRJ) and rocket based combined cycles (RBCC) vehicles. Past experience has shown that among the major fundamental problems to be solved in SC are the need for rapid (i.e., < 1 ms) mixing and combustion efficiency.
INGENITO, ANTONELLA, BRUNO, Claudio
openaire   +2 more sources

A Computational Method for Combustion in Supersonic Flows

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp; 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

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
openaire   +1 more source

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