High-strength hydrogen peroxide, a possible thrust-augmenting liquid, was injected in a tubular combustor and the resulting perform¬ance was studied. Combustor-inlet pressure and mass flow, and combustor-outlet temperature simulated operation of a 5.2 compressor-pressure -ratio engine at a flight Mach number of 0.6 and altitudes of 32,500 and 45,000 feet. Performance data were compared with similar data obtained with water injection, with 35-percent hydrogen peroxide injection, and with no liquid injection.nCombustor performance with 90-percent hydrogen peroxide injection was found to be superior to that with either water or 35-percent hydro¬gen peroxide injection. Greater mass-flow rates could be injected with no loss in combustion efficiency and without the occurrence of combustor blow-out. At all conditions, investigated, the 90-percent hydrogen per¬oxide was completely vaporized and 98 to 100 percent decomposed at the combustor outlet.
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