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Vibrational relaxation effects are examined for hypersonic nozzle air flows. A simple method of estimating the distribution of vibrational temperature along a nozzle is described and higher-order approximations discussed. Results are presented for hyperbolic axisymmetric nozzles with reservoir conditions 1000 ≤ p 0 ≤ 4000 p.s.i., 1000 ≤ T 0 ≤ 3000 °K. Vibrational freezing is shown to occur and to cause significant changes in the nozzle exit flow conditions.
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Stollery et al. (1962) studied this question.
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