Surface pressure measurement on a wing of SWIM by using PSP

PSP를 이용한 항공기 형상 모형 날개 표면 압력 측정

  • 정혜진 (과학기술연합대학원대학교, 항공기시스템공학과) ;
  • 권기정 (한국항공우주연구원)
  • Published : 2008.04.01


this study, three dimensional surface pressure distributions of SWIM whose main wing has NACA4412 airfoil with NACA0012 flaps were experimentally measured by pressure sensitive paint. Surface pressures on suction and pressure sides of the wing were measured by changing an angle of attack at a Reynolds number of 3.1x105 in KARI 1m subsonic wind tunnel. The experimental results showed that as an angle of attack increases minimum pressure region on a suction side moved from the wing root to the tip and low pressure region around trailing edge of the wing tip which causes wing tip vortex was observed. Although low pressure region at the tip still observed at an angle of attack 15 deg., other area on a suction side showed flat pressure distribution in a span-wise direction. It was also observed that the mean value of pressure coefficients was about 0.077 through a comparison between PSP and pressure taps at the same test conditions.

연구에서는 NACA4412익형으로 이루어진 주날개에 NACA0012플랩이 장착된 아음속 벽면효과 모형(SWIM)의 날개 표면 3차원 압력 분포를 압력감응페인트를 이용하여 시험적으로 연구하였다. 한국항공우주연구원의 아음속 풍동에서 레이놀즈수 3.1x105의 조건에서 시험 모형의 받음각 변화에 따른 날개 윗면 및 아랫면의 압력 분포를 측정하였다. 그 결과 받음각이 증가함에 따라 날개 윗면에서의 최저 압력 지점이 뿌리에서 끝단으로 이동을 하는 것을 관찰하였고, 날개 끝단의 뒷전에서도 끝단 와류를 일으키는 압력이 매우 낮은 지점도 관찰되었다. 그러나 실속각 이후인 받음각 15도의 경우 끝단 뒷전에서는 압력이 낮은 지점이 계속 관찰되었으나 그 이외의 부분은 스팬 방향 압력 분포가 편평하였다. 압력감응페인트와 더불어 압력공을 사용하여 날개의 코드 방향 2차원 압력분포도 측정 하여 비교하였고 두 시험에서 측정된 각 압력계수들의 차이의 평균은 약 0.077임을 확인하였다.



  1. Liu, T., Campbell, B. Burns, Sullivan, S. , "Temperature and Pressure-Sensitive Paints in Aerodynamics", Applied Mechanics Reviews, Vol. 50, No. 4, pp. 227-246, 1997
  2. Y. shimbo, K. Asai, H. Kanda and Y. Iijima, N. Komatsu, S. Kita and M. Ishiguro "Evaluation of Several Calibration Techniques for Pressure Sensitive Paint in Transonic Testing", 20th AIAA Advanced Measurement and Ground Testing Techmology Conference, AIAA-98-2502, 1998
  3. Tianshu Liu, M. Guille. and J.P. Sullivan "Accuracy of Pressure Sensitive Paint", 30th AIAA Fluid Dynamics Conference, AIAA-99-3785, 1999
  4. Bell, J.H., Shairer, E.T., Hand, L.A., Mehta, R.D., "Surface Pressure Measurements Using Luminescent Coatings", Annual Review of Fluid Mechanics, Vol. 33, pp. 155-206, 2001
  5. Liu, T. and Sullivan J.P. "Pressure and Temperature Sensitive Paints", Springer-Verlag, 2005
  6. Larry Goss, Grant Jones, Jim Crafton, Sergey Fonov "Temperature Compensation for Temporal (Lifetime) Pressure Sensitive Paint Measurements", Innovative Scientific Solutions, Inc. 2766 Indian Ripple Rd, Dayton OH, 45440
  7. Application Pakage OMS Version 3.0 : User's Guide, 2005
  8. Th.E. Labrufere, R.A. Maarsigh and J. Smith "Evaluation of Measured - Boundary - Condition Methods for 3D subsonic Wall Interference", National Aerospace Lab., Amsterdam (Netherlands), NLR TR 88072U, PB92-199991, pp. 56, 1988
  9. Long P. Yip and Gary L. Shubert, "Pressure distributions on a 1-by 3-meter semispan wing at sweep angles from 00 to 40' in subsonic flow", Langley Research Center, Hampton, Virginia, NASA Technical Memorandum D-8307, 1976

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