A note on the variation of vibrational temperature along a nozzle

Abstract

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 ≤ p0 ≤ 4000 p.s.i., 1000 ≤ T0 ≤ 3000 °K. Vibrational freezing is shown to occur and to cause significant changes in the nozzle exit flow conditions.