TY  - EJOU
AU  - Arun, M. 
AU  - Akhil, J. 
AU  - Noufal, K. 
AU  - Baby, Robin 
AU  - Babu, Darshitha 
AU  - Prakash, M. Jose 

TI  - EFFECT OF ASPECT RATIO ON SUPERCRITICAL HEAT TRANSFER  OF CRYOGENIC METHANE IN ROCKET ENGINE COOLING  CHANNELS
T2  - Frontiers in Heat and Mass Transfer

PY  - 2017
VL  - 8
IS  - 1
SN  - 2151-8629

AB  - 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.
KW  - <i>cryogenic rocket engine
KW  -  Regenerative cooling
KW  -  Heat transfer deterioration</i>

DO  - 10.5098/hmt.8.23