Investigation of Vortical Flow Field Visualization by Micro Water Droplet and Laser Beam Sheet

미세수적과 레이저 평면광에 의한 와류장의 가시화 연구

  • 이기영 (공군사관학교 기계공학과) ;
  • 손명환 (공군사관학교 항공우주공학과)
  • Published : 2002.03.01

Abstract

A new off-surface visualization method of using the micro water droplet and laser beam sheet was presented. About a size of 5 to TEX>$10\mu\textrm{m}$ micro water droplet could be made from home-style ultrasonic humidifier, A 3 W Argon ion laser and cylindrical lens were used to generate a laser beam sheet, which interrogate specific cross section of the vortical flow field. Application of this new visualization method was conducted in KAFA small-sized low speed wind tunnel of having the test section of 0TEX>$0.9 m(W){\times}$0.9 m(H){\times}2.1 m(L)$$$. Visualization results show this method relatively easy and safe flow visualization method for wind tunnel testing. Moreover, this method is also make up for the disadvantage of smoke visualization, and can be applied to higher flow velocity range than that of smoke visualization.

미세수적과 레이저 평면광을 사용하여 새로운 유동의 가시화 방법을 제안하였다. 미세수적은 약 5 내지 $10\mu\textrm{m}$ 크기로 가정용 초음파 가습기를 사용하여 생성시켰다. 조명은 3 W의 알곤 이온 레이저와 원통형 렌즈를 사용하여 레이저 평면광을 특정 와류장 단면에 형성시켰다. 이와 같은 새로운 유동의 가시화 방법을 측정부의 크기가 $0.9 m(W){\times}$0.9 m(H){\times}2.1 m(L)$$인 공군사관학교의 소형 풍동을 통하여 적용하였다. 가시화 결과를 통하여 미세수적을 이용한 새로운 가시화 방법이 풍동실험에 적용하기에 비교적 용이하며, 안전한 방법임을 보였다. 아울러 이 방법은 일반적으로 풍동실험에 적용되고 있는 스모크 가시화의 단점들을 보완함은 물론, 좀 더 높은 유동속도에서도 적용할 수 있었다.

Keywords

References

  1. Prentice, C. J., and Hurley, F. X., 1970,'Subsonic Flow Visualization Using Steam,'J. of Aircraft, Vol. 7, pp. 380
  2. Bisplinghoff, R. L., Coffin, J. B., and Holdeman, C. W., 1976, 'Water Fog Generation System for Subsonic FlowVisualization,' AIAA J., Vol. 14, pp. 1133-1135 https://doi.org/10.2514/3.7201
  3. Parker, A. G., and, Brusse, J. C., 1976,'New Smoke Generation for FlowVisualization in Low Speed WindTunnel,' J. of Aircraft, Vol. 13, pp. 57-58 https://doi.org/10.2514/3.44508
  4. Bouchez, J. P., and Goldstein, R. J., 1975,'Impingement Cooling from a Circular jetin a Cross Flow,' Int. J. Heat MassTransfer, Vol. 18, pp. 718-730
  5. Erickson, G. E., Schreiner, J. A., andRoeers, L. W., 'On the Structure,Interaction, and Breakdown Characteristicsof Slender Wing Vortices at Subsonic,Transonic, and Supersonic Speeds,'AIAA-89-3345, 1989
  6. 손명환, 이기영, 'Observation of VortexInteraction on the Yawed Delta Wingwith Leading Edge Extension by FlowVisualization and 5-Ho1e ProbeMeasurements,' 대한기계학회 추계학술대회 논문집, 2001
  7. 이기영, 손명환, 'Investigation of VortexInteractions over a Delta Wing with theLeading Edge Extension,' 한국군사과학기술학회 논문집, 2001
  8. Sohn, M. H, and Lee, K. Y., 'Experimental Investigation of Vortex Flowof a Yawed Delta Wing Having LeadingEdge Extension,' 20th AIAA AppliedAerodynamics Conference, 2002, to beappeared
  9. Gursul, I., and, Xie, W., 'Origin of Vortex Wandering over Delta Wings,' J. of Aircraft, Vol. 37, No. 2, 2000, pp. 348-350 https://doi.org/10.2514/2.2603
  10. Srigrarom, S., and Kurosaka, M.,'Shaping of Delta Wing Planform toSuppress Vortex Breakdown,' AIAA J.,Vol. 38, No. 1, 2000, pp. 183-186 https://doi.org/10.2514/2.939
  11. Srigrarom, S., and Kurosaka, M., 'SurfaceShaping to Suppress Vortex Breakdownon Delta Wing,' AIAA J., Vol. 38, No. 1,2000, pp. 186-187 https://doi.org/10.2514/2.940
  12. Merzkirch, W, Flow Visualization, 2nd ed.,1987, Academic Press INC
  13. Verhaagen, N. G., and Naarding, S. H. J.,'Experimental and Numerical Investigation ofVortex Flow over a Sidesliping Delta Wing,'J. of Aircraft, Vol. 26, No. 11, 1989, pp.971-978 https://doi.org/10.2514/3.45869