Abstract
The scramjet engine test facility (SETF) of the Korea Aerospace Research Institute is a blow-down, high enthalpy wind tunnel with a free-jet test cell. The free-jet test sections can reduce choking and test larger models compared with solid wall test sections, but the facility needs an excessive starting pressure ratio and is highly unpredictable because of the free-jet space. An air ejector system was designed to simulate a Mach 3.5 test condition. Quasi one-dimensional and computational analyses of the ejector were performed. The test results of the ejector well agree with the analysis results. The SETF showed a normal-shock efficiency of 58% at the Mach 3.5 condition. The air ejector system was modified to conduct a scramjet intake test with a Mach 6.7 condition. The normal-shock efficiency of the SETF was 40% with the Mach 6.7 condition. There was almost no change in the starting pressure ratio due to blockage.
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Yang Ji Lee is a Ph.D. candidate in Aerospace engineering at KAIST. She received her B.S. from Pusan National University in 2001 and M.S from Seoul National University in 2003. She has been working as a senior researcher in the Korea Aerospace Research Institute. Her main research interests cover hypersonic air-breathing engine designs, experiments, and hypersonic air-breathing engine test facility development.
Se Jin Kwon is a professor in the Aerospace engineering at KAIST. He received his B.S. from Seoul National University, M.S from KAIST and Ph.D. from University of Michigan, Ann Arbor in 1982, 1984, and 1991 respectively. His research interests include satellite and spacecraft propulsion, MEMS technology, monopropellant systems, non-intrusive diagnostics of turbulent reacting flow, and propulsion systems.
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Lee, Y.J., Kang, S.H., Yang, S.S. et al. Starting characteristics of the hypersonic wind tunnel with the mach number variation. J Mech Sci Technol 28, 2197–2204 (2014). https://doi.org/10.1007/s12206-014-0507-6
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DOI: https://doi.org/10.1007/s12206-014-0507-6