M. Arun, J. Akhil, K. Noufal, Robin Baby, Darshitha Babu, M. Jose Prakash*
Frontiers in Heat and Mass Transfer, Vol.8, pp. 1-9, 2017, DOI:10.5098/hmt.8.23
Abstract 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 Nusselt number is observed with aspect ratio. The efficacy of both Modified Jackson and Hall and Bishop
empirical correlations in predicting Nusselt number More >
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