Abstract
The technique and results of the experimental-theoretical study of gas dynamics, heat transfer and the structure of gas flow in the flowing channel of a model hypersonic air-ramjet engine are presented for Mach numbers M = (5; 6).
Highlights
At hypersonic flight speeds of rockets at low altitudes, it is supposed to use solid fuel airramjet engine
The processes of combustion and burning-out of the surface of the solid fuel element are determined by gas-dynamic and thermal parameters of flow in the flowing part of the engine
The presence of predictive estimates of the thermal state of the tract at the design stage of a specific design is necessary for a wellfounded choice of the ignition method and the provision sustainable combustion of solid fuel
Summary
At hypersonic flight speeds of rockets at low altitudes, it is supposed to use solid fuel airramjet engine. The air from the atmosphere, which enters through the air intake into the flowing channel of the engine with velocities M > 5 [1], is used as an oxidizer in the organization of combustion. The processes of combustion and burning-out (possibly, uneven) of the surface of the solid fuel element are determined by gas-dynamic and thermal parameters of flow in the flowing part of the engine. For design of engine facility, it is necessary to have of experimental studies data from that allow one to predict these parameters with a high degree of veracity for concrete designs [2]. The presence of predictive estimates of the thermal state of the tract at the design stage of a specific design is necessary for a wellfounded choice of the ignition method and the provision sustainable combustion of solid fuel. It is advisable to conduct preliminary studies with laboratory models, since full-scale stand experiments are costly
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