Abstract: A unique supersonic wind tunnel facility using resistance heaters has been built to simulate the operation of a scramjet over a range of Mach numbers of 3.0 to 4.5.A number of preliminary experiments results from calibration of both the facility and the various components were introduced.Based on the previous experience and the experimental results published worldwide,a new combustor configuration using cavity flame holder to create recirculation and promote the fuel/air mixing has been developed.And the combustion characteristics of the hydrogen have been investigated in the supersonic clean airstreams experimental facility.The effect of the hydrogen fuel equivalence ratio on the flame holding mechanism and combustion was studied.Furthermore,the ignition characteristics of kerosene using hydrogen pilot have been investigated.The effect of the injection locations and diameters on the kerosene combustion was also presented.