A model and numerical code are presented that describe quasi-one-dimensional compressible flows of gases with nonequilibrium of their vibrational and electronic energy modes/Chemical reaction channels are also modeled. Rate equations governing individual vibrational state populations are integrated as a function of streamwise position in a flow channel. Results are presented for flows of CO, NI, and NO in supersonic nozzles, and the conditions creating extreme nonequilibrium overpopulation of upper vibrational states are shown.Applications to 13 C isotope separation processes, to possible \ibration-to-electronic and electronic-to-electronic mode energy transfer lasers, are discussed.

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The results of an experimental study of blunt-body heat-transfer problems during entry into planetary atmospheres are presented. Equilibrium gas radiance and convective heattransfer rates were measured in several CO2-N 2 gas mixtures over a simulated flight velocity range (approximately) of 30,000 to 45,000 fps. An electrically driven shock tube was used to provide the simulated hypervelocity flight conditions. An unresolved problem concerning the apparent influence of gage surface material on measured convective heat-transfer rates is identified and discussed. The properties and performance of a total radiation cavity gage, used to obtain the gas radiance data, are described. It is shown that species concentrations in a CO2-N2 mixture have only a small effect on convective heating rates. A similar conclusion for gas radiance is inferred at flight velocities above 32,000 fps. The experimental results are compared with appropriate theoretical predictions and other experimental data and are used to predict stagnation-point radiative and convective heating for Venus entry trajectories. Nomenclature= calorimeter gage thickness ra = mass q -heat-transfer rate t = time y e -entry angle down from horizontal X = wavelength p = density Subscripts 1 = initial driven tube conditions 2 = behind incident shock W = wall R = radiative c -convective e = entry conditions (also equilibrium) / = flight conditions 0 = reference conditions * = stagnation conditions (also shock) oo = freestream conditions