Abstract
A coupled heat-transfer and flow model of a scramjet with a recooling cycle is established, and it includes supersonic combustion, combustion heating, and fuel cooling with real scramjet engine geometry and operating parameters. Under the most insufficient heat sink condition, flow and heat transfer characteristics are compared under real operating conditions during the recooling cycle and regenerative cooling. The comparison results indicate that the total heat sink (physical and recooling) in the recooling cycle adequately meets the cooling requirements of a scramjet under the most insufficient heat sink condition, and overtemperature can be well avoided in the recooling cycle. However, theMach number constraint can be easily activated in the recooling cycle and, therefore, the design of the second cooling passage merits some special attention.
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