Numerical simulation to static ground effect of delta wings with different sweep angles
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摘要:
采用数值模拟的方法研究了不同后掠角三角翼的静态地面效应，通过对气动力和流场特性的分析发现，随着后掠角的减小，地面对迎风面下流动的阻滞作用增强，地效导致的迎风面气动力增量也随之增大。地效导致的背风面气动力增量同样随着后掠角的减小而增大，但在不同的后掠角范围内，地效诱导背风面气动力增量的机理不同：中大后掠角下，其主要通过增强前缘涡强度诱导更大的吸力，而小后掠角下，其主要通过促进前缘涡向内扩散增大吸力范围。
Abstract:In this paper, the static ground effect of delta wings with different sweep angles is investigated by numerical simulation. The analyses of aerodynamic force and flow field characteristics show that in ground effect, the "block effect" of ground enhances the windward surface pressure; with the sweep angle decreasing, the "block effect" will be further strengthened, and thus the windward surface aerodynamic force increments due to ground effect increase. Besides, the leeward surface aerodynamic force increments due to ground effect also increase with the sweep angle decreasing, but flow physics is not the same for different sweep angles:for medium and high sweep angles, the leeward surface aerodynamic force increments due to ground effect are attributed to the increase of the suction induced by the enhanced leading edge vortex; for low sweep angles, they are attributed to the suction area extension, which results from the movement of the dispersive leading edge vortex.
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Key words:
- sweep angle /
- delta wing /
- static ground effect /
- windward surface /
- leading edge vortex
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图 2 三角翼表面网格拓扑、计算域尺寸和边界条件以及0.6CR位置沿翼面展向的压力分布
Figure 2. Surface mesh topology, dimensions and boundary conditions of computational domain, and spanwise pressure distributions of delta wing at 0.6CR
图 3 不同后掠角三角翼在静态地效下的气动特性
Figure 3. Aerodynamics of delta wings with different sweep angles under static ground effect
图 4 λ=75°、λ=55°和λ=35°三角翼在无界流场和静态地效下迎风面的Cp分布云图以及地效下的Cp增量云图
Figure 4. Windward surface Cp distribution contours of λ=75°, λ=55° and λ=35° delta wings in unbounded flow field with static ground effect and Cp increment contours of windward surface due to ground effect
图 5 典型后掠角三角翼在无界流场前缘涡附近的流线图和流向涡量ωx云图
Figure 5. Streamlines and streamwise vorticity ωx contours near leading edge vortex of typical delta wings with typical sweep angles in unbounded flow field
图 6 λ=75°、λ=55°和λ=35°三角翼在无界流场和静态地效下背风面的Cp分布云图以及地效下的Cp增量云图
Figure 6. Leeward surface Cp distribution contours of λ=75°, λ=55° and λ=35° delta wings in unbounded flow field with static ground effect and Cp increment contours of leeward surface due to ground effect
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[1] QU Q L, WANG W, LIU P Q, et al.Airfoil aerodynamics in ground effect for wide range of angles of attack[J].AIAA Journal, 2015, 53(4):1048-1061. doi: 10.2514/1.J053366 [2] CORDA S, STEPHENSON M T, BURCHAM F W, et al.Dynamic ground effects flight test of an F-15 aircraft:N95-33024[R].Washington, D.C.:NASA, 1994. [3] ROZHDESTVENSKY K V.Wing-in-ground effect vehicles[J].Progress in Aerospace Sciences, 2006, 42(3):211-283. doi: 10.1016/j.paerosci.2006.10.001 [4] QU Q L, JIA X, WANG W, et al.Numerical study of the aerodynamics of a NACA 4412 airfoil in dynamic ground effect[J].Aerospace Science and Technology, 2014, 38:56-63. doi: 10.1016/j.ast.2014.07.016 [5] SCHWEIKHARD W.A method for in-flight measurement of ground effect on fixed-wing aircraft[J].Journal of Aircraft, 1967, 4(2):101-104. doi: 10.2514/3.43804 [6] BAKER P A, SCHWEIKHARD W G, YOUNG W R.Flight evaluation of ground effect on several low-aspect-ratio airplanes:NASA-TN-D-6053[R].Washington, D.C.:NASA, 1970. [7] CURRY R E.Dynamic ground effect for a cranked arrow wing airplane:AIAA-1997-3649[R].Reston:AIAA, 1997. [8] CHANG R C, MUIRHEAD V U.Investigation of dynamic ground effect:N87-24410[R].Washington, D.C.:NASA, 1987. [9] CHANG R C, MUIRHEAD V U.Effect of sink rate on ground effect of low-aspect-ratio wings[J].Journal of Aircraft, 1987, 24(3):176-180. doi: 10.2514/3.45413 [10] CHANG R C.An experimental investigation of dyanmic ground effect[D].Lawrence, KS:University of Kansas, 1985. [11] LEE P H, LAN C E, MUIRHEAD V U.An experimental investigation of dynamic ground effect:NASA-CR-4105[R].Washington, D.C.:NASA, 1987. [12] LEE P H, LAN C E, MUIRHEAD V U.Experimental investigation of dynamic ground effect[J].Journal of Aircraft, 1989, 26(6):497-498. doi: 10.2514/3.45793 [13] QU Q L, LU Z, GUO H, et al.Numerical investigation of the aerodynamics of a delta wing in ground effect[J].Journal of Aircraft, 2014, 52(1):329-340. http://or.nsfc.gov.cn/handle/00001903-5/181352 [14] SPALART P, ALLMARAS S.A one-equation turbulence model for aerodynamic flows:AIAA-1992-0439[R].Reston:AIAA, 1992. [15] MORTON S.Detached-eddy simulations of vortex breakdown over a 70-degree delta wing[J].Journal of Aircraft, 2009, 46(3):746-755. doi: 10.2514/1.4659 [16] CUMMINGS R M, SCHÜTTE A.Detached-eddy simulation of the vortical flow field about the VFE-2 delta wing[J].Aerospace Science and Technology, 2013, 24(1):66-76. doi: 10.1016/j.ast.2012.02.007 [17] QIN Y P, QU Q L, LIU P Q, et al.DDES study of the aerodynamic forces and flow physics of a delta wing in static ground effect[J].Aerospace Science and Technology, 2015, 43:423-436. doi: 10.1016/j.ast.2015.04.004 [18] RIOU J, GARNIER E, BASDEVANT C.Compressibility effects on the vortical flow over a 65° sweep delta wing[J].Physics of Fluids, 2010, 22:035102. doi: 10.1063/1.3327286 [19] RODRIGUEZ O.Experimental investigations on the VFE-2 configuration at ONERA:RTO-TR-AVT-113 AC/323(AVT-113) TP/246[R].Washington, D.C.:NASA, 2009. [20] FRITZ W.Numerical solutions for the VFE-2 configuration on structured grids at EADS-MAS:RTO-TR-AVT-113 AC/323(AVT-113) TP/246[R].Washington, D.C.:NASA, 2009. [21] CHEN M Q, LIU P Q, GUO H, et al.Effect of sideslip on high-angle-of-attack vortex flow over close-coupled canard configuration[J].Journal of Aircraft, 2015, 53(1):1-14. doi: 10.2514/1.C033305 -
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