한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제22권5호
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  • Pages.97-106
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  • 2018
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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충격파 터널을 이용한 스크램제트 실험 기술

Scramjet Experimental Techniques Using a Shock Tunnel

  • Yang, Sungmo (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Kim, Keunyeong (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Chang, Eric Won Keun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Jin, Sangwook (The 4th R&D Institute - 5th Directorate, Agency for Defense Development) ;
  • Park, Gisu (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
  • 투고 : 2017.11.08
  • 심사 : 2018.01.02
  • 발행 : 2018.10.01
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초록

본 논문은 충격파 터널을 이용한 이중압축램프 흡입구 형상의 모델 스크램제트 시험에서 나타난 기술적 난제 및 그 해결 방안들을 정리하였다. 시험 설비 불시동, 격막 파편에 의한 유동 교란 및 모델 손상, 다중 분사에 따른 연료 제트 미발달, 그리고 짧은 시험 시간이 이에 해당한다. 파악된 기술적 난제들을 해결한 이후, 개선된 결과를 쉐도우그래프 이미지 및 저압관 끝단 전압력 측정 결과를 통해 확인하였다.

This paper summarizes the technical difficulties pertaining the double-compression ramp scramjet inlet model testing in a shock tunnel and their corresponding solutions. Four technical difficulties are identified: 1) test facility unstart, 2) flow disturbance and model damage due to the impact of diaphragm debris, 3) lack of fuel jet development due to multiple injection, and 4) short test time. After overcoming the identified technical difficulties, the improved results were confirmed through the results of shadowgraph images and shock tube end wall pressure.

키워드

참고문헌

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