Modeling supersonic combustion using a fully-implicit numerical methodA fully-implicit finite-volume algorithm for two-dimensional axisymmetric flows has been coupled to a detailed hydrogen-air reaction mechanism (13 species and 33 reactions) so that supersonic combustion phenomena may be investigated. Numerical computations are compared with ballistic-range shadowgraphs of Lehr (1972) that exhibit two discontinuities caused by a blunt body as it passes through a premixed stoichiometric hydrogen-air mixture. The suitability of the numerical procedure for simulating these double-front flows is shown. The requirements for the physical formulation and the numerical modeling of these flowfields are discussed. Finally, the sensitivity of these external flowfields to changes in certain key reaction rate constants is examined.
Document ID
19900055062
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maccormack, Robert W. (Stanford University CA, United States)
Wilson, Gregory J. (Stanford Univ. CA, United States)