Numerical study of shock-induced combustion in methane-air mixtures
The shock-induced combustion of methane-air mixtures in hypersonic flows is investigated using a new reaction mechanism consisting of 19 reacting species and 52 elementary reactions. This reduced model is derived from a full kinetic mechanism via the Detailed Reduction technique. Zero-dimensional computations of several shock-tube experiments are presented first. The reaction mechanism is then combined with a fully implicit Navier-Stokes computational fluid dynamics (CFD) code to conduct numerical simulations of two-dimensional and axisymmetric shock-induced combustion experiments of stoichiometric methane-air mixtures at a Mach number of M = 6.61. Applications to the ram accelerator concept are also presented.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
- OSTI ID:
- 5444708
- Report Number(s):
- N-94-14722; NASA-TM-106354; ICOMP-93-32; E-8138; NAS-1.15:106354; AIAA-Paper-93-1917; CNN: NCC3-233; RTOP 505-90-5K
- Country of Publication:
- United States
- Language:
- English
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ORGANIC
PHYSICAL AND ANALYTICAL CHEMISTRY
AIR
COMBUSTION
COMPUTERIZED SIMULATION
METHANE
CHEMICAL REACTIONS
HYPERSONIC FLOW
NAVIER-STOKES EQUATIONS
ALKANES
DIFFERENTIAL EQUATIONS
EQUATIONS
FLUID FLOW
FLUIDS
GASES
HYDROCARBONS
ORGANIC COMPOUNDS
OXIDATION
PARTIAL DIFFERENTIAL EQUATIONS
SIMULATION
THERMOCHEMICAL PROCESSES
400800* - Combustion
Pyrolysis
& High-Temperature Chemistry