Fluid Mechanics and Flight Mechanics

Junction flow horseshoe vortex control based on upstream cavity

  • LI Jian ,
  • ZHANG Hua ,
  • WU Xinggang
Expand
  • School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received date: 2016-09-18

  Revised date: 2016-11-21

  Online published: 2016-11-30

Supported by

National Natural Science Foundation of China (11372027)

Abstract

Two and three dimensional cavities have been studied by experimental and numerical simulation to control horseshoe vortex formed when the flow passes a cylinder-flat plate junction. The cavity is located on the flat plate upstream of the cylinder. The results indicate that both two and three dimensional cavities can delay boundary layer separation and weaken the horseshoe vortex. At the same time, the upstream surface pressure and adverse pressure gradient of cavity are both reduced, and at the downstream the pressure is increased while the global adverse pressure gradient is reduced. The study also indicates that the two dimensional cavity can reduce about 61.15%-66.51%, while the three dimensional cavity can reduce 66.65%-80.93%, of the horseshoe vortex strength. The effect of cavity geometry parameters, including distance, width and depth, is discussed. It is shown that the cavity distance plays major role in weakening the horseshoe vortex. The mechanism for controlling the horseshoe vortex by cavity is discussed. It is shown that the sub-layer of the incoming boundary layer which contains high vorticity is swallowed into the cavity to form the cavity vortex. The cavity vortex is transported to the downstream of the junction. As the cavity gets closer to the cylinder, more sub-layer of boundary layer will be swallowed into cavity. It is this cavity-effect that reduces the surface adverse pressure gradient upstream of the cylinder and diminishes the horseshoe vortex and separation region.

Cite this article

LI Jian , ZHANG Hua , WU Xinggang . Junction flow horseshoe vortex control based on upstream cavity[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(6) : 120796 -120796 . DOI: 10.7527/S1000-6893.2016.0304

References

[1] DEVENPORT W J, SIMPSON R L. Turbulence structure near the nose of a wing-body junction[C]//19th AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference. Reston: AIAA, 1987.
[2] DEVENPORT W J, SIMPSON R L. Time-dependent and time-averaged turbulence structure near the nose of a wing-body junction[J]. Journal of Fluid Mechanics, 1990, 210(2): 23-55.
[3] DEVENPORT W J, SIMPSON R L. LDV measurements in the flow past a wing-body junction[C]//4th International Symposium on Applications of Laser Anemometry to Fluid Mechanics. Lisbon: Instituto Superior Tecnico, 1988: 2-3.
[4] GRAZIANI R A, BLAIR M F, TAYLOR J R, et al. An experimental study of endwall and airfoil surface heat transfer in a large scale turbine blade cascade[J]. Journal of Engineering for Gas Turbines and Power, 1980, 102(2): 257-267.
[5] BLAIR M F. Heat transfer in the vicinity of a large-scale obstruction in a turbulent boundary layer[J]. Journal of Propulsion and Power, 1985, 1(2): 158-160.
[6] DEVENPORT W J, SIMPSON R L. Time-dependent structure in wing-body junction flows[M]. Turbulent Shear Flows 6. Berlin Heidelberg:Springer, 1989: 232-248.
[7] LIU Z H, XIONG Y, TU C X. Numerical simulation and control of horseshoe vortex around an appendage-body junction[J]. Journal of Fluids and Structures, 2011, 27(1): 23-42.
[8] LIU Z H, XIONG Y. Numerical simulation on the horseshoe vortex formation around the hull-sail junction of submarine[C]//2010 International Conference on Optoelectronics and Image Processing (ICOIP). Piscataway, NJ: IEEE Press, 2010, 2: 51-54.
[9] SEAL C V, SMITH C R, ROCKWELL D. Dynamics of the vorticity distribution in endwall junctions[J]. AIAA Journal, 1997, 35(6): 1041-1047.
[10] KHAN M J, AHMED A. Topological model of flow regime in the plane of symmetry of a surface-mounted obstacle[J]. Physics of Fluids, 2005, 17(4): 1089-1109.
[11] GRECO J J. The flow structure in the vicinity of a cylinder-flat plate junction: Flow regimes, periodicity, and vortex interactions[D]. Bethlehem: Lehigh University, 1990.
[12] PHILIPS D B, CIMBALA J M, TREASTER A L. Suppression of the wing-body junction vortex by body surface suction[J]. Journal of Aircraft, 1992, 29(1): 118-123.
[13] JOHNSON M J, RAVINDRA K, ANERS R. Comparative study of the elimination of the wing fuselage junction vortex by boundary layer suction and blowing[C]//32nd Aerosapce Sciences Meeting & Exhibit. Reston: AIAA, 1994: 10-13.
[14] 徐向南, 张华, 胡波. DBD涡流发生器及其在角区流动控制中的数值研究[J]. 航空学报, 2016, 37(6):1743-1752. XU X N, ZHANG H, HU B. Numerical study of DBD vortex generator and application in junction flow control[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(6): 1743-1752 (in Chinese).
[15] DEVENPORT W J, DEWITZ M B, AGARWAL N K, et al. Effects of a fillet on the flow past a wing body junction[J]. AIAA Journal, 1990, 28(12): 2017-2024.
[16] DEVENPORT W J, SIMPSON R L, DEWITZ M B, et al. Effects of a leading-edge fillets on the flow past an appendage-body junction[J]. AIAA Journal, 1991, 30(9): 2177-2183.
[17] NELSON R, GEORGE E, HAMID R. Effects of an upstream ribbed surface on the flow past a cylinder-flat plate junction[C]//AIAA 41st Aerospace Sciences Meeting and Exhibit. Reston: AIAA, 2003.
[18] KAIROUZ K A, RAHAI H R. Turbulent junction flow with an upstream ribbed surface[J]. International Journal of Heat and Fluid Flow, 2005, 26(5): 771-779.
[19] HORSTEN B, VELDHUIS L. Experimental and numerical results on cavity effects in juncture flow[C]//AIAA 38th Fluid Dynamics Conference and Exhibit. Reston: AIAA, 2008.
[20] KANG K J, KIM T, SONG S J. Strengths of horseshoe vortices around a circular cylinder with an upstream cavity[J]. Journal of Mechanical Science and Technology, 2009, 23(7): 1773-1778.
[21] ZAW ZAW O O. The investigation and control of 3D separated structures in juncture flow[D]. Beijing: Beihang University, 2011.
[22] ANSYS Inc. ANSYS FLUENT user's guide[M]. 2012.

Outlines

/