Yang -Ji LEE, Kyung Jae LEE, Inyoung YANG

DOI Number: N/A

Conference number: HiSST-2025-160

An integrated inlet for a Turbine-Based Combined Cycle (TBCC) engine capable of taking off from the ground and cruising at Mach 6 was designed. The integrated inlet was designed to operate at subsonic to hypersonic speeds, and this was verified by numerical analysis. In order to verify the performance of the designed integrated inlet, a ground test was performed using the Scramjet Engine Test Facility (SETF), a blowdown wind tunnel at the Korea Aerospace Research Institute. The test was performed under Mach 5 conditions, and this paper summarizes the performance test results of the integrated inlet under Mach 5 conditions. In addition, for the Mach 3.5 condition experiment where the engine
transition mode is executed, a Mach 3.5 nozzle of SETF was designed, and the applicability of the nozzle and the integrated inlet was examined by numerical analysis, and the results are also introduced in this paper.

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In Categories: 1.Events, 1.HiSST 2025, Testing & Evaluation
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