Numerical study of shock-induced combustion in methane-air mixtures

Conference · Tue Jun 01 00:00:00 EDT 1993

OSTI ID:5831639

Yungster, S; Rabinowitz, M J ^[1]

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1. NASA, Lewis Research Center, Cleveland, OH (United States)

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 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. 19 refs.

• OSTI ID: 5831639
• Report Number(s): AIAA-Paper-93-1917; CONF-930633-
• Resource Relation: Conference: Joint AIAA/SAE/ASME propulsion conference, Monterey, CA (United States), 28-30 Jun 1993
• Country of Publication: United States
• Language: English

Related Subjects

37 INORGANIC
ORGANIC
PHYSICAL AND ANALYTICAL CHEMISTRY
42 ENGINEERING
COMBUSTION
COMPUTERIZED SIMULATION
HYPERSONIC FLOW
NAVIER-STOKES EQUATIONS
NUMERICAL SOLUTION
CHEMICAL REACTIONS
FUEL-AIR RATIO
MACH NUMBER
METHANE
ALKANES
DIFFERENTIAL EQUATIONS
EQUATIONS
FLUID FLOW
HYDROCARBONS
ORGANIC COMPOUNDS
OXIDATION
PARTIAL DIFFERENTIAL EQUATIONS
SIMULATION
THERMOCHEMICAL PROCESSES
VELOCITY
400800* - Combustion
Pyrolysis
& High-Temperature Chemistry
420400 - Engineering- Heat Transfer & Fluid Flow