Abstract
The effects of rocket engine size on the effective exhaust velocity, for geometrically similar nozzles, are investigated as far as finite-rate chemistry and (gas-phase) radiation are concerned. Propulsion systems burning LOX/LH and LOX/LCH4 combinations are considered. The engine performance is estimated via a CFD code based on a particularly convenient formulation. It is found that finite-rate chemistry alone leads to performance steadily increasing with engine size, whereas introducing the effects of radiation reveals the occurrence of a maximum of effective exhaust velocity as a function of nozzle throat diameter. The exact quantification of radiation effects depends anyway to some extent on the modelling assumptions, as well as on the engine operating cycle.
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