Numerical analysis of internal flow thermal environment in an accelerating high

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Numerical analysis of internal flow thermal environment in an accelerating high–speed vehicle

Kim, Jae–Eun / Jeong, Seung–Min / Kim, Wie Dae / Choi, Jeong–Yeol / Hwang, Yoojun

Abstract A two-dimensional computational analysis was performed to assess the internal flow thermal conditions of a high-speed vehicle across seven distinct flight points spanning Mach numbers from 1.2 to 6.4. The investigation revealed that elevated pressure impeded inflow, leading to the formation of a substantial separation area on the ramps during the initial boost from Mach 1.2 to Mach 2.0. Progressing from Mach 3.0 to Mach 4.0, shock trains emerged in the isolator, with the supersonic internal flow stabilizing as the vehicle accelerated from Mach 5.0 to Mach 6.4. Specific regions, including the throat, a cavity, and the top of the nozzle, sustained consistently high temperatures, ranging from 1,700 K to 1,900 K at the highest flight speeds. Heat flux distribution remained uniform, staying below 100 kW/m² at flight points from Mach 1.2 to Mach 4.0. However, at Mach 5.0, 5.0, and 6.4, the heat flux escalated to peak values of 120 to 400 kW/m² and 1 MW/m², primarily concentrated at the throat, isolator, and cavity. Comparative analyses of René 41, Copper, and Inconel 625 revealed a heat flux disparity of approximately 20 times between René 41 and Inconel 625. These findings underscore the imperative for utilizing superalloys, such as Inconel 625, to ensure the secure operation and effective regenerative cooling of high-speed vehicles.