Abstract
This paper shows the design and analysis of an active impingement cooling system that can become the de facto choice for the hypersonic leading thermal protection system. In this study, we consider a case in which the leading edge is exposed to a high heat flux due to an external hypersonic Mach number of 7. An investigation is conducted to identify the best methodology to effectively cool the leading edge using Supercritical CO2 (sCO2) multi-jet impingement. Thermochemical nonequilibrium models are tested to study the influence of the air species model on aerodynamics and heat Transfer. The air 5 species Park’s model and 11 species Gupta’s model simulate hypersonic thermos-chemical nonequilibrium flow over a nose cone. Also, Fluid-Solid loosely coupled conjugate simulations are done with internal fluid carbon dioxide to test the capability of the numerical model. The results show that the 11-species model predicts higher heat flux compared to the 5-species model at high hypersonic Mach numbers. The conjugate numerical simulations are conducted at varying the relative coolant tube-to-leading-edge distance (H/D) between 1 and 5, and the impingement angles from 30o, and 60o. The study shows that the heat transfer performance can be enhanced with an increased coolant tube-to-leading-edge distance (H/D). Also, the heat transfer is increased with the varying impingement angle.
Published Version
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