Nonequilibrium performance losses are interpreted in terms of radical concentrations and extent of recombination throughout the expansion process. A brief description of the Bray method for determining the location of departure from equilibrium flow in a rocket nozzle is given. The analysis is applied to N2O4-aerozine, H2-O2 and H2-F2 propellants and a hypothetical H2-C12 system to obtain the point of effective freezing as a function of area ratio. The kinetic rates for the reactions occurring in the combustion process are discussed, and the values for the rates are included. (Author)
Nonequilibrium Rocket Nozzle Recombination Losses
1964
45 pages
Report
No indication
English
Physical & Theoretical Chemistry , Hydraulic & Pneumatic Equipment , Rocket Propellants , Nozzle gas flow , Analysis , Hydrogen , Oxygen , Chlorine , Liquid rocket propellants , Frozen equilibrium flow , Theory , Fluorine , Nonequilibrium flow , Recombination reactions , Combustion products , Nitrogen compounds , Tetroxides , Thermodynamics , Performance (Engineering) , Chemical reactions , Time , Aerozine