Structures and design of a new model of an axisymmetric solid fuel ramjet was developed. The ramjet has a polyclinic frontal air intake, a solid fuel gas generator, a combustion chamber and a nozzle. In accordance with the design a prototype was constructed for tests in a wind tunnel T-313 ITPM (Institute of Theoretical and Applied Mechanics). Various modes of solid fuel burning were tested in the model in external airflow at M=2 – 4. High values of internal thrust and resultant thrust minus drag coefficient were obtained.
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