Acknowledgement
본 연구는 방위사업청, 국방과학연구소의 선도형 핵심기술 연구개발 과제 중 '완제 터보팬 엔진 통합 개발 기술' 및 한국연구재단(NRF-2019M1A3A1A02076962)의 지원을 받아서 수행되었으며, 이에 감사드립니다.
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