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A hybrid approach of large-eddy simulation and immersed boundary method for flapping wings at moderate Reynolds numbers Guo-wei He Department of Aerospace.

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Presentation on theme: "A hybrid approach of large-eddy simulation and immersed boundary method for flapping wings at moderate Reynolds numbers Guo-wei He Department of Aerospace."— Presentation transcript:

1 A hybrid approach of large-eddy simulation and immersed boundary method for flapping wings at moderate Reynolds numbers Guo-wei He Department of Aerospace Engineering, Iowa State University And Institute of Mechanics Chinese Academy of Sciences Interface Problems Workshop Nov , North Carolina State University SAMSI: Program on Random Media

2 Objectives and goals Objectives: –Develop a hybrid approach of LES and IB to simulate plunge and /or pitching motions of an SD7003 airfoil at Re=60k –Investigate the flow field and the aerodynamics performance of an SD7003 airfoil in plunge and/or pitching motions Goals: –Develop a computational tool to predict the aerodynamics of flapping wing with experimental validation –Provide quantitative documentation of the flow field and the aerodynamics performance of flapping wings by computations LES=Large-eddy simulation, IB=immersed boundary

3 C C/4 Cp L.E. T.E. Free stream C : chord length; L.E. : leading edge; T.E. : trailing edge; Cp : center of pitching schematical illustration of a SD7003 airfoil A SD7003 airfoil in flapping motion A low speed airfoil with 8.5% thickness and 1.4% camber High frequency pitch and/or plunge motion

4 Laminar-turbulent transition over an SD7003 airfoil Fixed wings: turbulent transition with separation & reattachment - The 1st stage: receptivity; - 2: Linear growth stage; - 3. Nonlinear instabilities stage; - 4. Turbulence transition stage Flapping wings: compound with turbulence - Weis-Foghs clap and fling; - Leading-edge vortices; - Pitching-up rotation; - Wake-capture ; The challenges in numerical simulations: - Laminar-turbulent transition: turbulent flow and its transition - Plunge and/or pitching airfoil: moving boundary

5 Large-eddy simulation (LES) for turbulent & transitional flows LES vs DNS and RANS Time accurate LES in statistics –LES correctly predicts energy spectra Subgrid scale models are developed on energy budget equation –LES is being developed to predict frequency spectra or time correlations. That is a new challenge. 1. He GW, R. Rubinstein & LP Wang, PoF (2002) 2. He GW, M. Wang & SK Lele, PoF (2004) CostUnsteady StatisticsTurbulence models DNSUnacceptableTruly representiveNot necessary LESAffordablePredictableUniversal RANSCheapDifficult (URANS)Empirical

6 Filtered Velocity:, G is a filter. Large eddy simulation (LES) velocity =large scales + small scales computed modeled The filtered Navier-Stokes equation Key issues in LES: the filtered N-S equation 1.Subgrid scale modeling: energy dissipations filter sizes 2.Numerical algorithm: truncated errors grid sizes 3.Grid generation P. Moin, Inter. J. Heat & Fluid flows, 23 (2002) LES: a brief introduction

7 LES of an SD 7003 airfoil from Re=10, 000 and 1,000,000 The number of grid points exceeds the present computer capacity; Most of the points are used to resolve inner layers Wall models needed Flapping wings: moving boundaries –Grid embedding or multi-domain strategies : increase cost –Unstructured grids: negative impact on stability and convergence –Classic deformation or re-meshing strategies: additional overhead 1. U Piomelli & E. Balaras: Ann. Rev. Fluid Mech : Computer capacity: A Pentium III 933MHz workstation with 1GB of memory

8 Numerical methods for moving boundaries Boundary Conditions MeshComplex/moving boundary Computing turbulence Body- fitted method Directly imposed Body-fittedMesh-smoothing Or re-meshing Less efficient Overset method Directly imposed two or more sets meshes Hole cutting, interpolation in the overlapping region Being explored Immersed Boundary Method Forcing in body vicinity Cartesian mesh no more difficulty Efficiency, better conservation property Four different IB strategies for complex geometries A direction forcing at Lagrangian points Interpolation based on volume of fraction Explicit linear interpolation Ghost cell approach

9 A direct forcing approach (a IB method) Virtual forces are prescribed on the Cartesian grids to avoid body- fitting grids - represent the effects of body on flows - obtained to impose boundary conditions on body/flow interface IB for turbulence requires the near wall resolution in all 3 directions - local refinement Four essential steps: - track the locations of body/face interface in a Lagrangian fashion - formulate an adequate virtual force at the interface locations - transfer that force smoothly to the Eulerian grid nodes - time advancement of the Navier-Stokes equations in the Cartesian grids

10 A hybrid LES and IB method LES+IB: LES on the Cartesian grids for complex geometries Challenges: wall modeling on the Cartesian grids - body-fitting: wall modeling in the wall normal direction - Cartesian gird: wall modeling in all three directions Bulk flowsNear-wall turbulence Complex boundary geometries Challenges LESSGS modelsWall modelsBody-fitting gridsTwo IBLocal refinement (near wall resolution) Cartesian grids NS + forcing is Wall modeling Two LES+IBSGS modelsWall modelsWall models on Cartesian grids One

11 The planned work: wall modeling A SGS models with a damping function - Damping functions - Eddy viscosity model Boundary layer equations - wall stress - dynamic models Shear-dependent SGS models - homogeneous shear flows - wall turbulence

12 Wall treatments in IB/LES method SGS model: Smagorinsky model The wall damping function is defined as: Calculation of : –Minimal distance between Euler grid and Lagrangian point Calculation of : –Determined from the IB force in the tangent direction Illustration of IB force

13 The direct forcing method Solve the NS equation without forcing for intermediate velocity Interpolate for Lagrangian velocity Impose boundary conditions to NS for Lagrangian velocity Interpolate the force to Eulerian grids Solve the NS equation with force for Eulerian velocity rsh = pressure + SGS residual stress + viscosity term + convection term

14 The Navier-Stokes solver Spatial discretization –Second order finite volume method Temporal discretization –Fractional step method –Third order Runge-Kutta scheme is used for terms treated explicitly (the convective term and viscosity terms in span-wise direction) –Second order Crank-Nicholson is used for terms treated implicitly (the viscosity terms in stream-wise and cross-wise directions) Poisson solver –Pre-conditioned conjugate gradient solver

15 Validation: The 3D flow around circle cylinders –Body-fitting grids v.s. Cartesian grids –Lift and drag coefficients: vorticity behind cylinders Turbulent channel flows –Benchmark problem –Mean velocity profile and r.m.s velocity fluctuation

16 A slice of 3-D Cartesian mesh in z direction Stream and normal directions: the grids stretched to cluster points near surface Span-wise direction: uniform grids Domain size: 30Dx10Dx4D Boundary condition: in-flow: a uniform velocity profile out-flow: a convective boundary condition normal: shear free span-wise: periodic Shear free Convective BC u=1,v=0,w= Shear free Validation (I and II): Flow around a circular cylinder

17 Validation (I): flow around a stationary cylinder Vortex contour CdClSt Present1.445± Reference1.35± Time history of drag and lift coefficients for the flow past an rotating cylinder Re=100 Stationary

18 Validation (II): flow around a rotating cylinder CdClSt Present Overset Reference Re=200 Angular velocity= Time history of drag and lift coefficients for the flow past an rotating cylinder Vortex shedding behind an rotating cylinder

19 Validation (III): turbulent channel flow using LES and IBM Mean velocity profile R.m.s. velocity fluctuations Computation domain: Grid size : Reynolds number: in x, y, z. based on the wall shear velocity and the channel half-width Boundary condition: y=0.0,non-slip; y=h, non-slip periodic in x and z directions. SGS model: dynamic Smagorinsky SGS model IB method: direct forcing method in x, y, z. The IB interface is located at y=0.02 Simulation parameters M. Uhlmann, An immersed boundary method with direct forcing for the simulation of Particulate flows, JCP, 209 (2005)

20 Simulation parameters for SD 7003 airfoil The Reynolds number based on inflow velocity and chord length is : 60,000 Boundary conditions: –inflow: uniform velocity; outflow: convective boundary condition; –cross wise: shear free; span wise: periodic Four cases are simulated in present work : –Case1: flow past stationary airfoil SD7003, attack angle= –Case2: flow past plunging airfoil SD7003 –Case3: flow past combined pitching and plunging airfoil –Case4: flow past pitching airfoil SD7003 Flapping motion:

21 Simulation parameters: grid setting Two settings of grids are used in present case. Setting 1. –Domain size: 60C*60C*0.02C –The center of the airfoil is located at (30C, 30C) –Grid number: 472*332*4 –Mesh size: in the uniform region (IB region): 0.005, the increase proportion is 5% in stream-wise and is 10% in cross-wise, and is uniform in span-wise. Setting 2. –Domain size: 15C*10C*0.02C –The center of the airfoil is located at (5C, 5C) –Grid number: 570*384*4 –Mesh size: in the uniform region (IB region): 0.005, the increase proportion is 2% in stream-wise,is 4% in cross-wise, and is uniform in span-wise. Setting 1 is used for all the four cases. Setting 2 is used for case 2 and case 4.

22 Case1: stationary Lift and drag coefficients for the SD7003 airfoil at Re=60,000 Lift and drag coefficients consistentl with other author's Q3D results The transition point is 0.37C from the leading edge compared with 0.49C (W. Yuan, AIAA, 2005), due to the poor resolution near the leading edge Streamlines and turbulent shear stress for the SD7003 airfoil at Re=60,000, attack angle

23 Case1: stationary The dominant frequency range is from 0.2 to 3 Frequency spectra of the drag coefficient Frequency spectra of the lift coefficient Vortex contour Vortex contour of a stationary airfoil SD7003, attack angle=

24 Case 2: plunging (frequency=1.25, amplitude=0.05C) The wake vortex structure shows consistant with experiments results. Present case, vortex contour behind trailing edge Expt. From Michael V.OL, AIAA Dye injection side views for trailing and the near-wake

25 Case 2: plunging (frequency=1.25, amplitude=0.05C) Vortex contour of a plunging airfoil SD7003, frequency=1.25, amplitude=0.05C

26 Case 2: plunging (frequency=1, amplitude=0.1C) The mean Drag Coefficient CD=-0.105, thrust is generated by plunging; The mean Lift Coefficient CL=0.828 For drag coefficient, the dominant frequency is f =1,2 For lift coefficient, the dominant frequency is f =1 Time history of drag and lift coefficients Frequency spectra of the drag coefficient Frequency spectra of the lift coefficient

27 Case 3: Pitching The mean drag coefficient CD=0.941 The mean lift coefficient CL=1.235 For drag coefficient, the dominant frequency is f=2,4 For lift coefficient, the dominant frequency is f=2 Time history of drag and lift coefficients Frequency spectra of the drag coefficient Frequency spectra of the lift coefficient

28 Case 4: combined pitching and plunging motion The mean drag coefficient CD=0.564 The mean lift coefficient CL=1.248 For drag coefficient, the dominant frequency is f =1,2,3,4,5 For lift coefficient, the dominant frequency is f =1,2 Time history of drag and lift coefficients Frequency spectra of the drag coefficient Frequency spectra of the lift coefficient

29 Case 4: combined pitching and plunging Vortex contour of a combined pitching and plunging airfoil SD7003

30 Summary A hybrid approach of large-eddy simulation and immersed boundary method is developed Preliminary results for a SD 7003 airfoil at Re=60,000 show the promising of the hybrid approach Wall models coupled with immersed boundary method need to be developed


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