한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제46권4호
  • /
  • Pages.290-296
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  • 2018
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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초고속 비행체를 위한 준 자유흐름식 고공환경 모사시험설비의 상온시험 및 내부유동 해석

Cold Test and Internal Flow Analysis of Semi-Freejet Type High Altitude Environment Simulation Test Facility for the High-Speed Vehicle

  • Lee, Seongmin (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Yu, Isang (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Choi, Jiseon (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Oh, Junghwa (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Shin, Minkyu (Department of Aerospace Engineering, Graduate School at Chungnam National University) ;
  • Ko, Youngsung (Department of Aerospace Engineering, Chungnam National University)
  • 투고 : 2017.08.16
  • 심사 : 2018.03.19
  • 발행 : 2018.04.01
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초록

본 연구에서는 초고속 비행체 고공환경 모사시험 설비의 운용범위를 확인하기 위하여 시험모델의 형상변수에 따라 상온시험 및 수치해석을 수행하였다. 시험 모델의 형상변수로는 폐색율, 각도 및 길이 비를 고려하였다. 폐색율은 경사충격파와 팽창 팬의 영향으로 40% 이상의 영역에서 운용이 제한될 것으로 판단된다. 각도의 변수는 강한 충격파의 영향으로 45도 이하의 크기에서 모델을 선정해야함을 확인하였다. 길이의 변수는 모델직경대비 8배의 길이 변화에도 성능의 차이가 없었다. 최종적으로 원뿔형 시험 모델의 형상 변수에 따른 성능 데이터베이스를 확보하였으며, 준 자유흐름식 고공환경 모사설비의 운용 가능한 범위를 확인할 수 있었다.

In this study, the cold test and the numerical analysis were carried out according to the shape parameters of the test model in order to confirm the operation range of high altitude environment simulation test facility for the supersonic vehicle. The blockage ratio, angle and length ratio were considered as the design parameters. The blockage rate is expected to be limited in the region of more than 40% due to the normal shock and expansion fan. It was confirmed that the angle of model should be selected at the size of 45 degrees or less due to the influence of the strong shock wave. There was no difference in performance between the lengths of 8 times the model diameter. Finally, we obtained the performance database according to the shape parameters of the conical test model and confirmed the operable range of the semi-freejet type high altitude environment simulation test facility.

키워드

참고문헌

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