M. Arun, J. Akhil, K. Noufal, Robin Baby, Darshitha Babu, M. Jose Prakash

Frontiers in Heat and Mass Transfer (FHMT) 8 - 23 (2017)

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  up to aspect ratio 4. The efficacy  of  both Modified Jackson and Hall and Bishop empirical correlations  in predicting  Nusselt number is  tested for  cryogenic methane flowing in coolant  channels.