By R Johnson; R E Lipinski; U.S. Nuclear Regulatory Commission. Office of Nuclear Regulatory Research. Division of Engineering Technology

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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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