The tests of a hypersonic module with external flow at M = 4 in hot-shot wind tunnel.

The results of the calibration of the nozzle of a hot-shot wind tunnel with a new transonic insert for modeling the Mach number M = 4 are presented. This nozzle was used for preliminary tests of a hypersonic module with hydrogen combustion. It was found that hydrogen spontaneously ignites and its combustion leads to a fourfold increase in the static pressure in the model channel. Intensive pressure rising does not lead to disruption of the inflow in the air intake. [ABSTRACT FROM AUTHOR]