Accession Number : AD0648321
Title : SPECTROGRAPHIC ANALYSIS OF ROCKET NOZZLE FLOW.
Descriptive Note : Technical memo.,
Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
Personal Author(s) : Unger,H. J. ; Hill,F. K. ; Dickens,W. P.
Report Date : JAN 1967
Pagination or Media Count : 101
Abstract : Spectral analysis of the radiation from combustion products of solid propellants in supersonic flow is used to determine the composition and temperature of the gas. The spectrographic equipment and rocket apparatus are described and the experimental results obtained are compared with theory. The flow system examined is that of combustion gases passing through a rocket nozzle where the stagnation temperature and pressure correspond to 2500K and 75 atmospheres. The rapid expansion of the flow in the supersonic part of the nozzle gives rise to non-equilibrium conditions. The spectrometer is used to determine the concentration of one of the active species, CO2, as a function of distance down the nozzle. It is shown that the experimental results agree very closely with the prediction of flow performance based on chemical kinetics. Both emission and absorption spectra were obtained of CO2, CO and H2O in the range from 4 to 6.5 microns. The spectral measurements also enabled the static free-stream temperature of the gas to be determined. (Author)
Descriptors : (*ROCKET NOZZLES, NOZZLE GAS FLOW), (*NOZZLE GAS FLOW, *COMBUSTION PRODUCTS), SUPERSONIC FLOW, SOLID ROCKET PROPELLANTS, SPECTROSCOPY, STAGNATION POINT, CARBON DIOXIDE, CARBON MONOXIDE, TEMPERATURE
Subject Categories : Fluid Mechanics
Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE