Open Access
ARTICLE
EFFECT OF ASPECT RATIO ON SUPERCRITICAL HEAT TRANSFER OF CRYOGENIC METHANE IN ROCKET ENGINE COOLING CHANNELS
M. Arun, J. Akhil, K. Noufal, Robin Baby, Darshitha Babu, M. Jose Prakash*
Dept. of Mechanical Engineering, TKM College of Engineering,
Kollam- 691005, Kerala, India
* Corresponding Author: Email:
Frontiers in Heat and Mass Transfer 2017, 8, 1-9. https://doi.org/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 is tested for cryogenic methane flowing in coolant channels.
Keywords
Cite This Article
Arun, M., Akhil, J., Noufal, K., Baby, R., Babu, D. et al. (2017). EFFECT OF ASPECT RATIO ON SUPERCRITICAL HEAT TRANSFER OF CRYOGENIC METHANE IN ROCKET ENGINE COOLING CHANNELS.
Frontiers in Heat and Mass Transfer, 8(1), 1–9.