A fully implicit time accurate method for hypersonic combustion: application to shock-induced combustion instability |
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Authors: | Shaye Yungster Krishnan Radhakrishnan |
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Institution: | (1) Institute for Computational Mechanics in Propulsion, NASA Lewis Research Center, 44135 Cleveland, OH, USA;(2) NASA Lewis Research Center, NYMA, Inc, 44135 Cleveland, OH, USA |
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Abstract: | A new fully implicit, time accurate algorithm suitable for chemically reacting, viscous flows in the transonic-to-hypersonic
regime is described. The method is based on a class of Total Variation Diminishing (TVD) schemes and uses successive Gauss-Seidel
relaxation sweeps. The inversion of large matrices is avoided by partitioning the system into reacting and nonreacting parts,
but a fully coupled interaction is still maintained. As a result, the matrices that have to be inverted are of the same size
as those obtained with the commonly used point implicit methods. In this paper we illustrate applicability of the new algorithm
to hypervelocity unsteady combustion applications. We present a series of numerical simulations of the periodic combustion
instabilities observed in ballistic-range experiments of blunt projectiles flying at subdetonative speeds through hydrogenair
mixtures. The computed frequencies of oscillation are in excellent agreement with experimental data. |
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Keywords: | Reacting flows Unsteady combustion BDF method TVD schemes LU-SGS method |
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