Testing of solid fuel ramjet with measurement of thrust characteristics in aerodynamic facilities

Abstract

A design of an axisymmetric solid fuel ramjet consisting of a multi wedges nose air intake, solid fuel gas gene-rator, combustion chamber, and a nozzle, was developed. According to this design, a ramjet model for tests in the ground wind-tunnel facilities was fabricated. Experiments with solid fuel combustion were carried out in the Transit-M and T-313 wind tunnels, ITAM SB RAS, at air-flow Mach numbers М = 2.5−5.0. High values of the internal and net excess thrust were obtained.