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

  • 제43권2호
  • /
  • Pages.109-117
  • /
  • 2015
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

S-Duct 입구 형상에 따른 유동 특성에 관한 연구

A Study on Flow Characteristics of the Inlet Shape for the S-Duct

  • Lee, Jihyeong (Department of Mechanical Engineering, Hanyang University) ;
  • Choi, Hyunmin (Department of Mechanical Engineering, Hanyang University) ;
  • Ryu, Minhyoung (Department of Mechanical Engineering, Hanyang University) ;
  • Cho, Jinsoo (School of Mechanical Engineering, Hanyang University)
  • 투고 : 2014.10.07
  • 심사 : 2015.01.29
  • 발행 : 2015.02.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

덕트는 항공기의 내부엔진에 외부 공기를 흡입하기 위한 장치이다. 엔진 입구면의 레이더 반사량을 줄여 피탐지성을 감소시키기 위하여 S형태의 덕트를 가지게 되었다. S-Duct는 중심선의 곡률, 입구형상 등의 형상변수에 따라 엔진의 성능에 영향을 미친다. 본 연구에서는 RAE M 2129 S-Duct의 입구형상에 대하여 가로세로비의 변경에 따른 덕트 내부 유동에 대한 유동 특성을 알아보기 위해 전산해석을 수행하였다. S-Duct의 성능 평가 기준으로는 유동 왜곡계수를 사용하였다. 공력해석을 위해 상용해석 소프트웨어를 사용하였으며, 벽면에서의 역압력 구배의 영향으로 발생하는 유동박리와 2차 유동을 예측하기 위하여 $k-{\omega}SST$ 난류모델을 사용하였다. S-Duct의 Port side와 Starboard side 각각의 압력분포 값에 대하여 ARA의 실험값과 비교하여 본 연구에서 사용된 전산해석 기법의 타당성을 검증하였다. 해석 결과 모든 형상에 대하여 유동박리와 2차 유동이 발생하는 것을 확인하였다. 반원형 형태의 입구형상을 가지는 S-Duct가 뛰어난 성능을 보임을 확인하였다.

Aircraft needs an inlet duct to supply the airflow to engine face. A fighter aircraft that requires low radar observability has to hide the engine face in the fuselage to reduce the Radar Cross Section(RCS). Therefore, the flow path of the inlet duct is changed into S-shape. The performance of the aircraft engine is known to be influenced by the shape and the centerline curvature of the S-Duct. In this study, CFD analysis of the RAE M 2129 S-Duct has been performed to investigate the influence of aspect ratio of inlet geometry. The performance of the S-Duct is evaluated in terms of the distortion coefficient. To simulate the flow under adverse pressure gradient better, $k-{\omega}SST$ turbulence model is employed. The computational results are validated with the ARA experimental data. The secondary flow and the flow separation are observed for all computational cases, while the semi-circular geometry has been found to produce the best results.

키워드

참고문헌

  1. Plas, A.P., "Performance of a Boundary Layer Ingesting Propulsion System", MS Thesis, Massachusetts Institute of Technology, Dept of Aeronautics and Astronautics, June 2006
  2. Menzies, R., "Computational Investigation of Flows in Diffusing S-Shaped Intakes", Acta 76. Polytechnica, Vol. 41, No. 4. 2001
  3. Menzies R. D. D., "Investigation of S-shaped Intake Aerodynamics using Computational Fluid Dynamics," Ph. D. thesis, Department of Aerospace Engineering, University of Glasgow, 2002
  4. R.K. Sullerey, S. Mishra, A.M. Pradeep, "Application of boundary layerfences and vortex generators in improving performance of S-Duct diffuser,"J. Fluids Engineering 124, 2002 pp.136-142. https://doi.org/10.1115/1.1436096
  5. Yi J. S, Lee B. J, and Kim C. A, "Efficient Design Optimization of Vortex Generator in Subsonic Offset Inlet by Discrete Adjoint Approach," 20th AIAA Computational Fluid Dynamics Conference, Honolulu, Hawaii., 2011
  6. Sullerey, R.K. and A.M. Pradeep, "Active flow control in circular and transitioning S-Duct diffusers," ASME Journal of Fluids Engineering. 128, 2006, 1192-1203. https://doi.org/10.1115/1.2353263
  7. Anderson, B. H., "Vortex-Generator Installation Studies on SteadyState and Dynamic Distortion," Journal of Aircraft, Vol. 35, No. 4, 1998, pp. 513-520. https://doi.org/10.2514/2.2340
  8. Wellborn, S.R., Okiishi, T.H., and Reichert, B.A, "A Study of Compressible Flow through a Diffusing S-Duct," NASA Technical Memorandum 106411, December 1993
  9. Saha, K., Singh, N., and Seshadri, V.,"Computational Analysis of Flow Through Transition S-Diffusers: Effect of Inlet Shape," Journal of Aircraft, Vol. 44, No. 1, 2007, pp. 187-193. https://doi.org/10.2514/1.22828
  10. Manoj Kumar Gopaliya, Mahesh Kumar, Shailendra Kumar and Shiv Manjaree Gopaliya, "Analysis of performance characteristics of S-shaped with diffuser with offset," Aerospace Science and Technology Vol. 11, 2006, pp. 130-135
  11. Reichert, B. A., Hingst, W. R., and Okiishi, T. H., "An Experimental Comparison of Nonswirling and Swirling Flow in a Circular-to-Rectangular Transition Duct,"AIAA Paper 91-0342, 1991.
  12. Sirbaugh, J. R. and Reichert, B. A., "Computation of a Circular-to-Rectangular Transition Duct Flow Field," AIAA Paper 91-1741, 1991
  13. Tomas M. Berens, Anne-Laure Delot, Mattiias Chevalier, Jaap Van Muijden, Road A.Waaijer and Phil Tattersall, "GARTEUR AD/AG-43 Application of CFD High offset intake diffusers", GARTEUR Final Report, 2012,
  14. C.F. Smith, J.E. Bruns, G.J. Harloff, J.R. DeBonis," Three-dimensional compressible turbulent computations for a diffusing S-Duct," NASA CR 4392, 1991.
  15. Menter, F. R., "Two-equation eddy viscosity turbulence models for engineering applications," AIAA Journal, Vol.32, No. 8, 1994, pp. 1598-1605 https://doi.org/10.2514/3.12149
  16. N. E. May, "The prediction of intake/S-bend diffuser flow using various two-equation turbulence model variants including non-linear eddy viscosity formulations," ARA. Contractor Report M316/1, March 1997
  17. AGARD, "Air Intakes for high Speed Vehicles", AGARD ADVISORY 270, Fluid Dynamics Panel Working Group 13, 1991
  18. NG YOW THYE ,"A Study of the Flow in an S-shaped Duct," Ph. D. thesis, Department of Mechanical Engineering, National University of Singapore, 2009
  19. Kim. H. S, Choi H. M, and Cho J. S, "Aerodynamic Characteristics of the Blended-Wing-Body for the Position and Aspect Ratio of the Inlet and Outlet of an Embedded Distributed Propulsion System," J. of Korea Society for Aeronautical & Space Sciences,, Vol. 40, No.6, 2012.6, pp. 467-474. https://doi.org/10.5139/JKSAS.2012.40.6.467