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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: 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.

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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.



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