Nonequilibrium Effects in Kerosene-Oxygen Rocket Nozzle Flows,

摘要

Nonequilibrium flow calculations were made for a small rocket engine burning kerosene and oxygen. Such rockets can be used in the laboratory for producing plumes under controlled experimental conditions. A time-dependent finite-difference technique was used to calculate the chemical nonequilibrium flow throughout the nozzle, including nonequilibrium conditions both upstream and downstream of the nozzle throat. Cases were computed for oxidizer/fuel ratios from 1.6 to 5. The results indicated that the principal chemical species (CO2, H2O and CO) deviated from equilibrium by about 20% at the nozzle exit. Of particular importance is the nonequilibrium gas static temperature, which is approximately 400K less than equilibrium conditions.