Sangbin HAN, Hyung Mo BAE, Jihyuk KIM, Dongkyun LEE, Kyeongho LEE, Sunghwan YIM, Hyung Hee CHO

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST 2024 – 0057

In this study, the heat transfer characteristics of the radome were analyzed to determine the thermal stability of the radome considering the flight scenario of an air-launched missile. Numerical analysis was performed for a flight time of 50 seconds for five cases considering two flight scenarios. The radome wall temperature indicates that the heat load is highest at the radome stagnation point. Also, as the Mach number increases, the temperature of the radome wall increases significantly due to aerodynamic heating. However, the higher the altitude, the lower the temperature at a similar Mach number. Pyroceram 9606, the material of choice for the radome walls in this study, was thermally stable in all cases, given the wall thicknesses assumed in the study.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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