Accession Number : AD0709842
Title : CONVECTIVE HEAT TRANSFER IN ROCKET ENGINES. PART 5. NON-UNIFORM BOUNDARY LAYER EFFECTS.
Descriptive Note : Technical rept.,
Corporate Author : ROCKET PROPULSION ESTABLISHMENT WESTCOTT (ENGLAND)
Personal Author(s) : Parkinson,R. C.
Report Date : MAY 1970
Pagination or Media Count : 43
Abstract : The effects of chemical non-equilibrium in the boundary layer, of temperature variation and compressibility assumptions, and of systematic errors in the estimated transport properties upon the heat transfer in rocket engines have been investigated. Hydrogen recombination and hydrogen/hydroxyl recombination appear to be the important reactions in determining the degree of chemical equilibrium occurring within the boundary layer. The important effect of chemical reaction upon the heat transfer is to increase the available enthalpy drop across the boundary layer. There appear to be systematic errors in the current methods of calculating the transport properties of combustion gas mixtures containing hydrogen as a component. (Author)
Descriptors : (*LIQUID PROPELLANT ROCKET ENGINES, CONVECTION(HEAT TRANSFER)), (*COMBUSTION CHAMBER GASES, CONVECTION(HEAT TRANSFER)), RECOMBINATION REACTIONS, NOZZLE GAS FLOW, REACTION KINETICS, ENTHALPY, BOUNDARY LAYER, HEAT OF REACTION, TRANSPORT PROPERTIES
Subject Categories : Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE