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

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
권호 표지
DOI QR코드

DOI QR Code

Visualization Study of High-Incidence Vortical Flow over the LEX/Delta Wing Configuration with Sideslip

옆미끄럼을 갖는 LEX/삼각 날개 형상에 대한 높은 받음각 와유동의 가시화 연구

  • 손명환 (공군사관학교 항공우주공학과) ;
  • 이기영 (공군사관학교 기계공학과)
  • Published : 2002.08.01
Download PDF
⟨ Previous Next ⟩

Abstract

An off-surface flow visualization experiments have been performed to investigate the flow field over a delta wing with the leading edge extension(LEX). The model is a flat wing with $65^{\circ}$ sweepback angle. The free stream velocity is 6.2 m/s, which corresponds to Reynolds number of $4.4\times10^5$ based on the wing root chord. The angle of attack and sideslip angle range from $16^{\circ}\sim28^{\circ}$ and $0^{\circ}\sim-15^{\circ}$, respectively. The visualization technique of using the micro water-droplet and the laser beam sheet enabled to observe the vortical flow structures, which can not be obtained by 5-hole probe measurements. With sideslip angle, the interaction and breakdown of the LEX and wing vortices was promoted in the windward side, whereas, it was suppressed in the leeward side.

옆미끄럼이 있는 조건에서 LEX를 갖는 삼각날개의 와류 특성을 유동의 가시화에 의한 실험적 방법으로 연구하였다. 모델은 $65^{\circ}$ 후퇴각의 갖는 평판 날개이다. 자유 유동속도는 6.2 m/s이며, 이 속도와 날개뿌리 시위를 기준으로 한 레이놀즈 수는 $4.4\times10^5$ 이다. 받음각 범위와 옆미끄림각 범위는 각각 $16^{\circ}\sim28^{\circ}$와 $0^{\circ}\sim-15^{\circ}$ 이다. 미세수적과 레이저 평면광에 의한 가시화는 오공 프로브에 의한 측정으로부터 얻을 수 없었던 보다 자세한 와유동 구조를 관찰 할 수 있도록 하였다. 옆미끄럼각이 있는 경우, 바람쪽은 LEX 와류와 날개 와류의 상호작용과 붕괴가 촉진되는 반면, 바람반대쪽은 두 와류의 상호작용과 붕괴가 억제되었다.

Keywords

References

  1. Malcolm, G. N., "Impact of High-Alpha Aerodynamics on Dynamic Stability Parameters of Aircraft and Missiles," AGARD-CS-114, paper No. 2, 1981.
  2. 손명환, 이기영, "Vortex Flow Control in Modern Aerodynamics," 한국항공우주학회지 제28권 7호, 2000.,10., pp. 119-130.
  3. Olsen, P. E., and Nelson, R. C, "Vortex Interaction over Double Delta Wings at High Angles of Attack," AIAA paper 89-2191, July 1989.
  4. Hebbar, S. K, Platzer, M. F., and Fritzelas, A. E., "Reynolds Number Effects on the Vortical Flow Structure Generated by a Double Delta Wing," Exp. in Fluids, Vol. 28, 2000, pp. 206-216. https://doi.org/10.1007/s003480050380
  5. Verhaagen, N. G., and Naarding, S. H. J., "Experimental and Numerical Investigation of Vortex Flow over a Sideslipping Delta Wing," J. of Aircraft, Vol. 26, No. 11, 1989, pp. 971-978. https://doi.org/10.2514/3.45869
  6. Grismer, D. S., and Nelson, R. C., "Double-Delta-Wing Aerodynamics for Pitching Motions with and without Sideslip," J. of Aircraft, Vol. 32, No. 6, 1995, pp. 1303-1311. https://doi.org/10.2514/3.46879
  7. Hebbar, S. K., Platzer, M. F., and Chang, Wen-Huan, 'Control of High-Incidence Vortical Flow on Double-Delta wings Undergoing Sideslip," J. of aircraft, Vol. 34, No. 4, 1997, pp. 506-513. https://doi.org/10.2514/2.2220
  8. Verhaagen, N. G, "Effects of Reynolds Number on the Flow over 76/40-deg Double-Delta Wings," AIAA Paper, 1999.
  9. Lee, Gwo-Bin, Shih, C, Tai, Yu-Chong, Tsao, T., Liu C, Huang, A. and Ho, Chih-Ming, "Robust Vortex Control of a Delta Wing by Distributed Microelectromechanical-Systems Actuators, " J. of Aircraft, Vol. 37, No. 4, 2000, pp. 697-706. https://doi.org/10.2514/2.2655
  10. Payne, F. M., Ng, T. T. and Nelson, R. C, "Visualization and Wake Surveys of Vortical Flow over a Delta Wing, " AIAA J., Vol. 26, No. 2,1988, pp. 137-143. https://doi.org/10.2514/3.9864
  11. 손명환, 이기영, "Vortex Flow and Aerodynamic Load Characteristics of the Delta Wing/LEX Configuration in Sideslip," 한국항공우주학회지 Vol. 30, No. 2, 2002, pp. 1-9.
  12. 손명환, 백동기, 임기철, 박민우, "Visualization of the Vortical Wakes of a Three-Dimensional Wing Using the Smoke-Wire Technique," 한국항공우주학회지, Vol. 18, No. 1, 1990, pp. 81-91.
  13. 이기영, 손명환 "Visualization of Vortical Flow Field by Water Droplet of Ultrasonic Humidifier, " 한국항공우주학회 2001 추계학술대회 초록집, pp. 485-490.
  14. Erickson, G. E., Schreiner, J. A., & Rogers, L. W., "On the Structure, Interaction, and Breakdown Characteristics of Slender Wing Vortices at Subsonic, Transonic, and Supersonic Speeds," AIAA Paper 1989, AIAA-89-3345.