한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제21권6호
  • /
  • Pages.57-63
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  • 2017
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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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플라즈마 분사장치를 활용한 초고속 비행체의 항력감소 기초 실험

Fundamental Experiments of Drag Reduction for a High Speed Vehicle Using Plasma Counterflow Jets

  • Kang, Seungwon (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Choi, Jongin (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Lee, Jaecheong (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Huh, Hwanil (Department of Aerospace Engineering, Chungnam National University)
  • 투고 : 2016.11.24
  • 심사 : 2017.10.04
  • 발행 : 2017.12.01
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초록

본 연구에서는 플라즈마 분사장치를 활용하여 항력감소를 위한 기초 실험을 수행하였다. 가시화 장비와 항력 측정 장비를 이용하여 기초 실험 장치를 구성하였다. 자유유동 환경에서 분사되는 플라즈마 역분사 제트를 가시화하기 위한 방법으로 쉴리렌 기법을 활용하였다. 가시화 실험 결과를 통해 플라즈마 제트의 침투와 유동구조 변화를 관찰하였다. 항력감소 가능성을 측정하기 위한 방법으로 로드셀을 이용한 측정을 수행하였다. 그 결과 초음속 자유유동 조건에서 역으로 분사되는 플라즈마를 통해 항력이 6.2% 감소함을 보였다.

In this study, the fundamental test for drag reduction is carried out by using a plasma generator. Fundamental test setup is constructed of visualization and drag measurement system. The schlieren technique is used to visualize the plasma counterflow in supersonic flow. The penetration of the plasma jet and the change of the flow structure are observed through visualization results. Load cell is used to confirm possibility of drag reduction. Results show that drag was reduced by 6.2% using plasma jet in supersonic flow.

키워드

참고문헌

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