Abstract: Results of an experimental study of 3D inlets and the scramjet module are presented.The scramjet module consists of an inlet and a combustion chamber.The module is designed to study the flow structure,to obtain the inlet characteristics, and to study the mutual effects of the combustor and the inlet,fule ignition and combustion (hydrogen and hydrocarbon fuels). The tests was conducted in the blowdown wind tunnel at Mach numbers from 2 to 6 and unit Reynolds numbers from 8 to 54 million and in the hot-shot wind tunnel at Mach numbers M=6 and 7.2 and unit Reynolds numbers from 10 to 32 million (Tt=1500~2500K).