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- W59064411 abstract "Ramjet propellant selection must be based upon the mission for which the engine is intended. Properties upon which selection is generally based are shown to be, a) gravimetric heating value, b) volumetric heating value and, c) energy release per pound of engine air flow. Which of these properties is significant depends upon whether the mission is long-range and requires aerodynamic lift in addition to that generated by the vehicle body or whether a booster or intercept function is desired. For hypersonic ramjet missions, consideration of several additional fuel properties is required. The high stagnation air temperatures encountered require evaluation of propellant thermal stability. If the fuel is to be used as a coolant, a large heat-sink capacity is also desirable. Propellants applicable to the hypersonic ramjet are considered, and trends in combustor designs for such engines are discussed. Considerable experience has been accumulated on the combustion problems of supersonic ramjets. Efficient burner configurations have been evolved for solid, liquid, and gaseous propellants having a wide variety of physical and chemical properties. By appropriate design of the burner hardware, point-design combustion efficiencies between 85 and 100 per cent seem attainable with all fuels of interest. Several problem areas are indicated which require increased activity before complete propellant evaluation for hypersonic ramjets is possible. These include the study of condensed-phase exit nozzle flow and the dissociation-recombination of ramjet combustion gases." @default.
- W59064411 created "2016-06-24" @default.
- W59064411 creator A5078466878 @default.
- W59064411 date "1960-01-01" @default.
- W59064411 modified "2023-09-23" @default.
- W59064411 title "PERFORMANCE EVALUATION OF RAMJET PROPELLANTS" @default.
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- W59064411 doi "https://doi.org/10.1016/b978-1-4831-9626-8.50018-0" @default.
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