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

  • 제30권3호
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  • Pages.1-7
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  • 2002
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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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논문 : LEX 가 델타형 날개의 표면압력분포에 미치는 영향

Papers : Effects of LEX on the Surface Pressure Distribution over a Delta Wing

  • 발행 : 2002.05.31
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초록

LEX를 가진 델타형 날개 모델을 사용한 풍동실험을 통하여 LEX가 델타형 날개 윗면의 표면압력분포에 미치는 영향에 대한 연구를 수행하였다. 풍동실험의 유속은 40m/sec, 전압과 전온도는 각각 101Pa, 278K이었으며, 단위길이당 레이놀즈 수는 $1.76{\times}10^6$이었다. LEX는 날개의 표면압력분포를 매우 많이 변화시키었다. LEX가 없는 경우에 비하여 표면압력의 피크치가 시위 앞부분에서는 감소하였으나 뒷부분으로 갈수록 그리고 받음각이 증가할수록 피크치도 증가하였다. 스팬방향 압력구배도 시위 앞부분에서는 완만하였으나 뒤로 갈수록 증가하였다. 또한 LEX가 있는 경우에는 모든 위치에서 받음각의 증가에 따라 표면압력 피크치도 거의 선형적으로 증가하였다.

An experimental study was conducted to investigate the effects of leading edge extension(LEX) on the surface prssure distribution over a delta wing in a subsonic wind tunnel. Freestream velocity was 40m/sec and Reynolds number per meter was 1.7x$10^6$ with total pressure of 101Pa and total temperature of 278K. LEX changed the surface pressure distribution on the wing dramatically. Comparing with the results without LEX, the peak of pressure distribution decreased on the front chordwise location but it turned to increase on the rear chordwise location with increase of the angle of attaci. The spanwise gradient of the pressure distribution also increased in the rear chordwise location. Without LEX, the peak of pressure distribution increased and decreased irregularly with increase of the angle of attack at each chordwise location, but LEX made it increased almost linearly with increase of the angle of attack at all of the chordwise locations.

키워드

참고문헌

  1. Kern, S. B., "Vortex Flow Control Using Fillets on a Double-Delta Wing," J. of Aircraft, Vol. 30, No. 6, Nov.-Dec. 1993, pp. 818-825. https://doi.org/10.2514/3.46422
  2. Norris, M. H and Lan, C. E., "An Experimental Investigation of the Effects of Leading Edge Extensions and Forebody Flow Separations on the Forebody-Vortex Induced Aerodynamics of a Generic Fighter Configuration," AIAA-91-3251-CP, pp. 381-389.
  3. Lee, B. H and Marineau-Mes, S., "Load Measurements on the Leading Edge Extension, Wing, and Body of an F/A-18," J. of Aircraft, Vol. 35, No. 2, Mar.-Apr. 1998, pp. 295-300. https://doi.org/10.2514/2.2299
  4. Faler, J. H. and Liebovich, S., "Disrupted States of Vortex Flow and Vortex Breakdown," The Physics of Fluids, Vol. 20, 1977, pp. 1385-1400. https://doi.org/10.1063/1.862033
  5. Payne, F. M., Ng., T. T., Nelson, R. C., and Schiff, L. B., "Visualization and Wake Surveys of Vortical Flow over a Delta Wing," AIAA Journal, Vol. 26, No. 2, Feb. 1988, pp. 137-143. https://doi.org/10.2514/3.9864
  6. Honkan, A. and Andreopoulos, J., "Instantaneous Three-Dimensional Vorticity Measurements in Vortical Flow over a Delta Wing," AIAA Journal, Vol. 35, No. 10, Oct. 1997, pp. 1612-1620. https://doi.org/10.2514/2.20
  7. Ericsson, L. E., "Vortex Characteristics of Pitching Double-Delta Wings," J. of Aircraft, Vol. 36, No. 2, Mar.-Apr. 1999, pp. 349-356. https://doi.org/10.2514/2.2464
  8. Boer, R. G. and Cunningham, A. M., "Low-Speed Unsteady Aerodynamics of a Pitching Straked Wing at High Incidence - Part I : Test Program," J. of Aircraft, Vol. 27, No. 1, Jan. 1990. pp. 23-30. https://doi.org/10.2514/3.56824
  9. Cunningham, A. M. and Boer, R. G., "Low-Speed Unsteady Aerodynamics of a Pitching Straked Wing at High Incidence - Part II : Harmonic Analysis," J. of Aircraft, Vol. 27, No. 1, Jan. 1990. pp. 31-41. https://doi.org/10.2514/3.45893
  10. Hoeijmakers, H. W. M., Vaatstra, W., and Verhaagen, N. G., "Vortex Flow over Delta and Double-Delta Wings," J. of Aircraft, Vol. 20, No. 9, Sept. 1983, pp. 825-832. https://doi.org/10.2514/3.44949
  11. Erickson, G. E., Schreiner, J. A., and Rogers, L. W., "On the Structure, Interaction, and Breakdown Characteristics of Slender Wing Vortices at Subsonic, Transonic, and Supersonic Speeds," AIAA paper 89-3345, Aug. 1989.
  12. Bannink, W. J., Some Recent Results on Vortex Bursting on a Delta Wing at High Subsonic Speeds, AGARD-CP-437, Vol. 1, 1988.
  13. Schrader, K. F., Reynolds, G. A., and Novak, C. J., "Effects of Mach Number and Reynolds Number on Leading-Edge Vortices at High Angle-of-Attack," AIAA paper 88-0122, Jan. 1988.