Calculation and Analysis of the Flow Passing through a Multi-Element Wing
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摘要: 采用中心差分的有限体积方法和分区技术求解了N-S(Navier-Stokes)方程,在分区求解技术中采用了满足通量守恒的内边界耦合条件.分析讨论了三维襟翼的绕流流场,对"剪刀差"处的三维分离进行了探讨,初步揭示了绕流的主要特征及对附近物面压强的影响.同时,分析了三维襟翼前缘的分离流动.
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关键词:
- 襟翼 /
- 分离流动 /
- 纳维尔-斯托克斯方程
Abstract: The N-S equation is solved using a finite volume method with central difference scheme and a domain decomposition technique, an internal coupling condition satisfying the conservation of flux is used in the domain decomposition method. The complex flow field passing through a three-dimensional wing with flap is analyzed, the main features of the separated flow field are shown, it is discussed the formation of the flap side-edge vortex and its influence on the aerodynamics characteristics; meanwhile, the flap leading-edge bubble separated flow is also illustrated.-
Key words:
- flaps /
- separated flow /
- Navier-Stokes equations
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[1] Pulliam T H, Steger J L. Implicit finite difference simulation of three dimensional compressible flow[J]. AIAA J, 1980, 18(2):159~167. [2] Baldwin B S, Lomax H. Thin layer approximation algebraic model for separated turbulent flows. AIAA 78-257,1978. [3] Jameson A, Schmidt W, Turkel E. Numerical solutions of the Euler equations by finite volume methods using Runge-Kutta time stepping schemes. AIAA 81-1259,1981. [4] Swanson R C, Turkel E. Artificial dissipation and central difference schemes for Euler and Navier-Stokes equations. AIAA 87-1107,1987. [5] Omar E, Zierten T, Hahn M, et al. Two dimensional wind-tunnel test of a NASA supercritical airfoil with various high lift systems. NASA CR-2215, 1974. [6] Dallmann U, Herberg Th, Gebing H, et al. Flow field diagnostics:Topological flow changes and spatio-temporal flow structure. AIAA 95-0791,1995. -
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