The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study,combustion efficiency had been found poor less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscalecombustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found very effective. Then a laboratory scale ram combustor was fabricated and combustion tests were carried out mainly at the simulated condition of Mach5. A vitiation technique was used to simulate a high temperature of 1263 K. The test results indicate that ignition, flame stability, and combustion efficiency were not significant, but the NO{sub}x emissions are a critical problem for the ram combustorat Mach 5 condition.
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