A numerical study of hydrogen-air combustion within a supersonic boundary layer

Conference · Wed Jan 01 00:00:00 EST 1992

OSTI ID:5663666

Figueira da silva, L F; Deshaies, B; Champion, M ^[1]

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1. Ecole Nationale Superieure de Mecanique et d'Aerotechnique, Poitiers, (France)

A numerical study of the ignition and spread of combustion within a supersonic boundary layer is presented for case where ignition is triggered by viscous dissipation and/or wall temperature effects. Three important regions are found in the boundary layer in the streamwise direction. They are: (1) an induction region where the process is mainly controlled by streamwise convection and chemical kinetics in the presence of transverse molecular transports, (2) a thermal runaway region corresponding to a large chemical heat release, (3) a flame region which develops at the end of the thermal runaway region where a flame is stabilized at the outer edge of the boundary layer. The whole chemical process becomes endothermic for large values of free-stream Mach numbers due to intense dissociation effects. 11 refs.

• OSTI ID: 5663666
• Report Number(s): AIAA-Paper-92-0338; CONF-920157-
• Resource Relation: Conference: 30. American Institute of Astronautics and Aeronautics (AIAA) aerospace sciences meeting and exhibit, Reno, NV (United States), 6-9 Jan 1992; Other Information: Research supported by SEP
• Country of Publication: United States
• Language: English

Related Subjects

08 HYDROGEN
HYDROGEN FUELS
COMBUSTION KINETICS
BOUNDARY CONDITIONS
BOUNDARY LAYERS
FINITE ELEMENT METHOD
IGNITION
MACH NUMBER
RAMJET ENGINES
REACTION KINETICS
SUPERSONIC FLOW
TEMPERATURE EFFECTS
CHEMICAL REACTION KINETICS
ENGINES
FLUID FLOW
FUELS
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
KINETICS
LAYERS
NUMERICAL SOLUTION
SYNTHETIC FUELS
VELOCITY
083000* - Hydrogen- Combustion- (1990-)