Flow through a Rocket Nozzle with and without Vibrational Equilibrium

A procedure is outlined for calculating the maximum changes in the exhaust velocity of gases which can be introduced during flow through a rocket nozzle as the result of vibrational time lags. Representative calculations have been carried out for a number of propellant systems. These calculations indicate that the vibrational time lags cannot produce changes in exhaust velocity which exceed a few percent. The numerical values of the changes are found to depend not only on the nature of the gases but also on the occurrence or non-occurrence of chemical reaction during flow.