Experimental study of the control agent flow parameters in the channel, simulating the ramjet air flow duct

Abstract

Abstract This article presents the results of the experimental study of heat transfer when the supersonic air flow interact with the surface of the ramjet model air flow duct in the range of Mach numbers M = 5 – 7. Experimentally obtained temperature distribution along air flow duct of a ramjet shown. The temperature along the axisymmetric model of the air flow duct was measured using the designed hot probe. Distribution of the Mach number along the symmetry axis of the model air flow duct is obtained numerically. A comparison of the numerical and experimentally obtained values of the Mach number showed their satisfactory agreement