The effect of cooling channel cross sectional shape on the flow distribution of hydrocarbon fuel in SCRamjet was researched. Parallelogram shape cooling channel was taken as an example to compare with rectangular channel. 3-D modelling of the flow and heat transfer of hydrocarbon fuel in multiple cooling channels under supercritical pressure was done. Under different channel aspect ratios

the parallelogram channel was better both in flow distribution and cooling effect because of the larger heat exchange area. The maximum heated wall temperature fell 226 K at most. Then the angle of the parallelogram channel was also important. Larger angle design led to larger heat exchange area and improved the flow distribution and cooling effect. The maximum heated wall temperature fell 287 K when the channel angle increased from 105° to 150°. The effect of practical headers was also taken into consideration. The parallelogram channel design was validated under the joint influence of U-type headers and non-uniform thermal boundary condition

showing good application value. The results of this work offer possible solution to the cooling channel design of SCRamjet.