Abstract
Spontaneous Raman spectroscopy was utilized in an experimental investigation of vibrational nonequilibrium in hydrogen-oxygen rocket engines. Oxygen temperatures were measured at subsonic, sonic, and supersonic portions of the nozzle flow. Rotational temperatures were determined from rotational Raman scattering. Both rotational and vibrational temperatures were determined from vibrational-rotational Raman spectra. Rotational temperatures from the two types of Raman scattering agree within the very large experimental error present. Vibrational temperatures are in agreement with rotational temperatures within the experimental error as well. Vibrational Raman spectroscopy is shown to be a valid means of estimating rotational temperatures within the rocket chamber and at low nozzle area ratios. Flowfield effects due to vibrational nonequilibrium are concluded to be minor. (Author)
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