Facilities for Scramjet Improvement

Abstract : The description of TSNIIMASH facilities for improvement of scramjet inlets and combustion chambers is presented. For research of inlets it is offered to use a large-scale hypersonic wind tunnel U - 306-3 working at Mach numbers 2 3 4, 6, 8, 10 with a nozzle-exit diameter of 1,2 m. The description of this facility activity scheme and its basic distinctive parameters are given. It is marked, that the facility Y - 306-3 can be used to test large-scale models and model flying velocities and dynamic head for different altitudes. For analysis of hydrogen - air or hydrocarbon - air mixtures supersonic combustion in scramjet combustion chambers is offered to use a special test-bed on the basis of facility U - 12 modernization. The test-bed includes the pressure vessel of a variable volume, succeeded hypersonic nozzles on Mach numbers 4, 6, 8, 10, combustion chamber, exit nozzle and exhaust system. The maximal pressure in the pressure vessel can reach 50 MPa. The combustion chamber has the cylindrical shape with an interior diameter of 0.5 m and length of 9 m. It allows to test real injection systems during tests. The system of an exhaust includes a gas holder with diameter of 3.2 m and volume of 180 squared m. She also is equipped with potent vacuum pumps, which one can create rarefaction ^ 1 Pa for rather short time. The problems of scramjet creation are analyzed, which one can be resolved on the facilities.