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EFFECT OF ASPECT RATIO ON SUPERCRITICAL HEAT TRANSFER OF CRYOGENIC METHANE IN ROCKET ENGINE COOLING CHANNELS
Frontiers in Heat and Mass Transfer
The supercritical turbulent flow of cryogenic methane flowing in a rocket engine cooing channel is numerically analysed by imposing constant heat flux at the bottom surface of the channel. The calculation scheme is validated by comparing the results obtained with experimental results reported in literature. The heat transfer coefficient is influenced by the strong variation in thermophysical properties of methane at super critical pressure. An increasing trend in the average value of Nusseltdoi:10.5098/hmt.8.23 fatcat:xihljrhnnjfrzb3bx3ayruzprq