Computation vs. Experiment for High-Frequency Low-Reynolds Number Airfoil Pitch and Plunge

McGowan, Gregory; Gopalarathnam, Ashok; Ol, Michael V.; Afb, Wright-Patterson; Edwards, Jack R.; Fredberg, Daniel

doi:10.2514/6.2008-653

Cited by 33 publications

(27 citation statements)

References 8 publications

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“…Good agreement between the computed and the experimental phase averaged velocity fields in the near wake (x/c = 1.5) of McGowan et al [67] is observed in Fig. 15.…”

Section: Plunging Sd7003 Airfoilsupporting

confidence: 54%

“…The airfoil is set at a small static angle of attack α 0 = 4 o in the center of a 100c × 100c computational domain, where c = 600lu is the chord of the foil. The flow over a plunging SD7003 at high-frequency, low-amplitude motions has been recently investigated both numerically and experimentally [63,64,65,66,67]. The plunging motion is characterised with a reduced frequency k = πf c/U ∞ = 3.93 and a non-dimensional amplitude h 0 =ĥ 0 /c = 0.05 leading to a maximum excursion of 21.5 o in the induced angle of attack.…”

Section: Plunging Sd7003 Airfoilmentioning

confidence: 99%

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PROTEUS: A coupled iterative force-correction immersed-boundary cascaded lattice Boltzmann solver for moving and deformable boundary applications

Falagkaris

Ingram

Markakis

et al. 2018

Computers & Mathematics with Applications

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Many realistic fluid flow problems are characterised by high Reynolds numbers and complex moving or deformable geometries. In our previous study, we presented a novel coupling between an iterative force-correction immersed boundary and a multi-domain cascaded lattice Boltzmann method, Falagkaris et al., and investigated flows around rigid bodies at Reynolds numbers up to 10 5 . Here, we extend its application to flows around moving and deformable bodies with prescribed motions. Emphasis is given on the influence of the internal mass on the computation of the aerodynamic forces including deforming boundary applications where the rigid body approximation is no longer valid. Both the rigid body and the internal Lagrangian points approximations are examined. The resulting solver has been applied to viscous flows around an in-line oscillating cylinder, a pitching foil, a plunging SD7003 airfoil and a plunging and flapping NACA-0014 airfoil. Good agreement with experimental results and other numerical schemes has been obtained. It is shown that the internal Lagrangian points approximation accurately captures the internal mass effects in linear and angular motions, as well as in deforming motions, at Reynolds numbers up to 4 · 10 4 . In all cases, the aerodynamic loads are significantly affected by the internal fluid forces.

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“…Good agreement between the computed and the experimental phase averaged velocity fields in the near wake (x/c = 1.5) of McGowan et al [67] is observed in Fig. 15.…”

Section: Plunging Sd7003 Airfoilsupporting

confidence: 54%

Section: Plunging Sd7003 Airfoilmentioning

confidence: 99%

PROTEUS: A coupled iterative force-correction immersed-boundary cascaded lattice Boltzmann solver for moving and deformable boundary applications

Falagkaris

Ingram

Markakis

et al. 2018

Computers & Mathematics with Applications

View full text Add to dashboard Cite

show abstract

“…The reduced frequency is usually calculated by 2πfr h c/U ∞ . However, in the present work it is defined as πfr h c/U ∞ , in order to be consistent with that used in the experimental and other CFD results [13,20,21]. Thus, the kh value in the present work is half of that in Ref.…”

Section: A Validation Of Force Predictionsupporting

confidence: 53%

“…In order to study the design of a more practical case of lifting airfoil, the asymmetric SD7003 airfoil [19] was used in our simulations, while previous experimental works [13,20,21] The computed vorticity contours at selected physical time steps for the plunge motion is presented in Fig. 5(a) and Λ Nm+2 =0 clearly provides a poor accuracy.…”

Section: B Validation Of Flow Analysis For Wake Profilesmentioning

confidence: 99%

Unsteady Adjoint Approach for Design Optimization of Flapping Airfoils

Lee

Liou

2012

AIAA Journal

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“…Flows over SD7003 airfoil with different motions have been experimentally studied by McGowan et al 39,40 and numerically studied by Visbal et al 41 In this case, the detail of the flow field around the airfoil is investigated with a prescribed motion at low Reynolds number condition. The Reynolds number based on the chord length of the airfoil is 10 000.…”

Section: Flow Over a High-frequency Plunging Sd7003 Airfoilmentioning

confidence: 99%

A diffuse‐interface immersed boundary method for simulation of compressible viscous flows with stationary and moving boundaries

Sun

Yang

Chen

et al. 2019

Numerical Methods in Fluids

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In this paper, a diffuse-interface immersed boundary method (IBM) is proposed for simulation of compressible viscous flows with stationary and moving boundaries. In the method, the solution of flow field and the implementation of boundary conditions are decoupled into two steps by applying the fractional step technique, ie, the predictor step and the corrector step. Firstly, in the predictor step, the intermediate flow field is resolved by a recently developed gas kinetic flux solver (GKFS) without consideration of the solid boundary. The GKFS is a finite volume approach that solves the Navier-Stokes equations for the flow variables at cell centers. In GKFS, the inviscid and viscous fluxes are evaluated as a single entity by reconstructing the local solution of continuous Boltzmann equation. Secondly, in the corrector step, the intermediate flow field is corrected by the present diffuse-interface IBM. During this process, the velocity field is firstly corrected by the implicit boundary condition-enforced IBM so that the no-slip boundary condition can be accurately satisfied. After that, the density correction is made by an iterative approach with the help of the continuity equation. Finally, the correction of the temperature field is made in the same way as that of the velocity field. Good agreements between the present simulations and the reference data in literature demonstrate the reliability of the proposed method. KEYWORDS compressible viscous flows, diffuse interface, fractional step technique, gas kinetic flux solver, immersed boundary method, moving boundary problem Int J Numer Meth Fluids. 2020;92:149-168. wileyonlinelibrary.com/journal/fld 149 150 SUN ET AL.Recently, to improve the computational efficiency and reduce the complexity of gas kinetic BGK scheme, a GKFS was proposed by Sun et al. 9 Different from the conventional gas kinetic BGK scheme, a straightforward way to approximate the nonequilibrium distribution function was developed in GKFS. That is, the nonequilibrium term is calculated by the difference of equilibrium distribution functions at the cell interface and its surrounding points. It has been proven that the GKFS is quite attractive because it can give almost the same results compared with the gas kinetic BGK scheme, while it only takes about 60% of the computational time of the latter. This scheme can be well applied to simulate both incompressible and compressible flows, even up to hypersonic flows. However, like most of the body-fitted solvers, the GKFS encounters difficulties in simulating flows with complex and moving boundaries due to the tedious mesh generation and remesh process. As an alternative approach, the immersed boundary method (IBM) has been widely utilized to tackle the solid boundary condition of these kinds of problems due to its simplicity and flexibility.The IBM was first presented by Peskin 10,11 in 1970s to simulate the incompressible blood flow in heart valves. The basic concept of IBM is that the deformation or displacement of the solid boundary will generate ...

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Computation vs. Experiment for High-Frequency Low-Reynolds Number Airfoil Pitch and Plunge

Cited by 33 publications

References 8 publications

PROTEUS: A coupled iterative force-correction immersed-boundary cascaded lattice Boltzmann solver for moving and deformable boundary applications

PROTEUS: A coupled iterative force-correction immersed-boundary cascaded lattice Boltzmann solver for moving and deformable boundary applications

Unsteady Adjoint Approach for Design Optimization of Flapping Airfoils

A diffuse‐interface immersed boundary method for simulation of compressible viscous flows with stationary and moving boundaries

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