By Paul A. Libby (auth.), M. Champion, B. Deshaies (eds.)

This quantity comprises chosen shows of the IUTAM Symposium on `Combustion in Supersonic Flows' held in Poitiers on the Ecole Nationale Supérieure de Mécanique et d'Aérotechnique (ENSMA) from 2 to six October 1995.
The shows specialise in 4 major issues on the topic of combustion in supersonic streams and useful matters suitable to the improvement of latest propulsion structures: primary reports of premixed and unpremixed combustion, fluid dynamics facets of supersonic combustion, useful platforms together with Scramjet, Ramaccelerators and Pulsed Detonation Engines, and the appliance of detonation to propulsion.
very important growth has been made within the figuring out of neighborhood mechanisms which enable combustion to be stabilized in a supersonic move; particularly, quite a few mechanisms managed by means of blending, chemical kinetics, viscous heating and surprise waves at the moment are good pointed out. regardless of the trouble of constructing experimental paintings on supersonic combustion, an excellent set of experimental info is now to be had, permitting validation of theoretical research and versions. the most features of modelling of turbulent combustion in excessive velocity flows have been mentioned, together with the impact of turbulent fluctuations at the chemistry-controlled section of combustion and the applicability of flamelet versions to excessive pace flows. the total diversity of numerical methods is roofed together with Direct Numerical Simulation, huge Eddy Simulation, k-epsilon and surprise monitoring tools. a substantial attempt has been made to generalize those the way to the remedy of supersonic reactive flows and to advance new numerical equipment taking into consideration the newest theoretical paintings and a greater knowing of the underlying physics.

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Extra resources for IUTAM Symposium on Combustion in Supersonic Flows: Proceedings of the IUTAM Symposium held in Poitiers, France, 2–6 October 1995

Example text

In relation to current efforts devoted to the development of a supersonic air-breathing propulsion system, numerous studies have been carried out to assess the main difficulties involved in employing supersonic combustion. Several experiments have been realized in axisymmetric and two-dimensional configurations, and various computations have been performed to investigate in detail the difficulties associated with combustion in high-speed flows. These studies have shown that finite-rate chemistry effects and their coupling with turbulence are the dominant features of such reacting flows.

16]), is employed to discretize the governing equations. A modified Newton method is used to obtain a converged solution at each streamwise step, and an adaptative mesh refinement copes with the gradients in the transverse direction [17]. Thermodynamical, transport and chemical properties are calculated using the CHEMKIN II package [7] [12]. The initial and boundary conditions used for the calculations of boundary and mixing layers and jets are: For boundary layer problems we use the Blasius (Schlichting [18]) selfsimilar compressible profiles of u, T and v as inflow conditions.

0 Figure 10. Induction length as a function of the equivalence ratio, comparison with the values obtained from the thermal explosion induction time. 2. INFLUENCE OF THE EQUIVALENCE RATIO ON THE INDUCTION LENGTH It was shown in the previous paragraph that, for given mixture composition, the induction length within the boundary layer is a function of the freest ream Mach number and temperature via the chemical time sensitivity to the maximum temperature in the flow, which is approximately given by equation 26.

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