Abstract
A platelet transpiration is introduced to strengthen the cooling effect in reattachment region for opposing jet in hypersonic flow. This introduced means can strengthen the local thermal protection performance without leading to an overall enhanced cooling intensity, being helpful on saving the total cooling gas. The two-equation SST k–ω turbulence model has been utilized to study the heat reduction and flow fields of the simplified combinational nose-tip in hypersonic flow. At first, the influence of individual pore are analyzed. The obtained results show that transpiration gas forms a cooling film adhering to the body surface which isolates the serious aerodynamic heating. The transpiration pores which are located on upstream margin of the reattachment point exhibit the best cooling effect. Then, the combination nose-tip is improved. A limited amount of pores are arranged in the reattachment region merely to strengthen the local cooling efficiency. The cooling capacity is obviously promoted with transpiration gas in contrast to that without transpiration. The peak heat flux reduces more than 12% with the mass flux of total cooling gas only promotes by 7.5%. Finally, the study demonstrates that the simplified model with limited amount of pores promote the cooling efficiency in contrast to that without transpiration.
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