New Method for Computing Performance of Choked Reacting Flows and Ram-to-Scram Transition

An improved method has been developed to compute the thrust of a dual-mode scramjet, which is an engine with a combustor that operates both subsonically and supersonically. This strategy applies to any internal flow that can be modeled one-dimensionally. To handle the mathematical singularity at the location of thermal choking, the simple Shapiro method is expanded to create a new method that includes finite-rate chemistry and high-temperature gas properties. A forward shooting method is employed to find appropriate initial conditions for integration of the governing equations, which results in a unique transonic (choked) condition capable of reaching a supersonic state at the end of the domain. Solutions of the governing equations are computed using the propulsion code MASIV, which has been integrated into a hypersonic vehicle flight dynamics code. Computations for both ram-mode and scram-mode operations are compared to experimental results. Predictions are made for flight conditions of a hypersonic vehi...

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