Abstract
Many methods have been widely carried out to increase fuel heat sink to meet the cooling requirement of an airbreathing hypersonic vehicle. In particular, the recooling cycle has been newly proposed for an actively cooled scramjet to increase fuel heat sink. Fuel heat sink (cooling capacity) is repeatedly used to indirectly increase the fuel heat sink through secondary cooling in recooling cycle. The performance of recooling at off-design conditions is evaluated based on a coupled heat transfer and flowmodel of a scramjet with recooling cycle. The design principle of the recooling cycle under off-design conditions with a great range of Mach numbers and equivalence ratios is determined. The results show that the recooling cycle possesses variable heat sink increment capacities, and it can meet heat sink requirement at all conditions.
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