Authors: Anbuselvan K.K.N.
Recently, Deep and Jagadeesh published a paper on understanding the aerothermodynamic effects of chromium coating over a large angle blunt cone test model at hypersonic flow conditions. The article concludes that the heat-flux at stagnation point increases by 25.6%, the temperature at stagnation region increases by 5%, and the shock stand-off distance increases by 17% with chromium coating. These findings appear to be ambiguous due to inconsistencies in the manner of calculating the free-stream values, the inappropriate use of measurement techniques and incorrect analysis of experimental data which have been elucidated in this comments.
Comments: 4 Pages.
[v1] 2019-03-30 07:54:00
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