Supersonic Flow of Chemically Reacting Gas-Particle Mixtures. Volume I. A Theoretical Analysis and Development of the Numerical Solution,
LOCKHEED MISSILES AND SPACE CO INC HUNTSVILLE AL HUNTSVILLE RESEARCH AND ENGINEERING CENTER
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This report describes a numerical solution for chemically reacting supersonic gas-particle flows in rocket nozzles and exhaust plumes. The gas-particle flow solution is fully coupled in that the effects of particle drag and heat transfer between the gas and particle phases is treated. Gas and particulates exchange momentum via the drag exerted on the gas by the particles. Energy is exchanged between the phases via heat transfer convection andor radiation between the gas-particle phases. Basic assumptions made in the development of the governing equations are similar to those employed by previous investigators. The primary exception is the treatment of chemical effects in the gas phase. Thermochemistry calculations chemical equilibrium, frozen or chemical kinetics are shown to be uncoupled from the flow solution and, as such, can be solved separately. The solution to the set of governing equations is obtained by utilizing the method of characteristics. The equations cast in characteristic form are shown to be formally the same for ideal, frozen, chemical equilibrium and chemical non-equilibrium reacting gas mixtures. The characteristic directions for the gas-particle system are found to be the conventional gas Mach lines, the gas streamlines and the particle streamlines.
- Fluid Mechanics
- Combustion and Ignition
- Solid Propellant Rocket Engines