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An estimation of vibrational frozen temperatures in the testing region for the range of running conditions used in the von Karman Institue Longshot hypersonic wind tunnel is presented. To assess the extent of the nonequilibrium effects caused by the vibrational freezing, the static temperature and pressure variation along the nozzle are calculated. An approximate method has been developed to find the influence of vibrational relaxation on the temperature and pressure along the stagnation line between a bow shock and a body. This has been done to determine the errors involved in calculating test section conditions in which the flow is assumed to be in equilibrium and to aid selection of an appropriate technique of measuring stagnation temperature required to study the nozzle wall turbulent boundary layer in the Longshot tunnel. (Author)