Numerical/experimental study of a wingtip vortex in the near field

Dacles‐Mariani, Jennifer; Zilliac, Gregory G.; Chow, Jim; Bradshaw, P.

doi:10.2514/3.12826

Cited by 454 publications

(173 citation statements)

References 15 publications

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“…It has succeeded in predicting flows with separation in the boundary layer. A variation of the model, SARC, which reduces the eddy viscosity in regions of high vorticity, 7,14) is also used in this study. In this study, a simple combination using the minimum of the vorticity and strain rate is utilized in the modification.…”

Section: Flow Solver and Turbulence Modelmentioning

confidence: 99%

CFD Validation for High-Lift Devices: Three-Element Airfoil

Murayama

Zhong

Mukai

et al. 2006

Trans. Japan Soc. Aero. S Sci.

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In this study, the accuracy of structured and unstructured mesh CFD codes in simulating the flow around a threeelement high-lift configuration (slat, main wing, and flap) is assessed, and mesh dependency and effect of turbulence models are studied. In the first part of the study, the results of two structured mesh CFD codes and an unstructured mesh CFD code using the same turbulence model are compared and discussed. A mesh refinement approach is also used to examine the dependency of numerical accuracy on the density of unstructured meshes. By properly distributing mesh points in an unstructured mesh, the detail in flow physics is obtained. It is also shown that the quantitative prediction of the vortex in the slat cove is an important factor that affects accuracy. In the second part of the study, three turbulence models are compared using one of the structured mesh CFD codes. All turbulence models can produce similar flowfields. However, several differences are seen in the separated regions, especially in the slat cove. Commonly used turbulence models, Spalart-Allmaras model and Menter's SST model, produce similar aerodynamic forces at lower angles of attack. At higher angles of attack, the SST model gives better results for the present computations. It is found that the maximum lift and the angle at which the stall occurs are very sensitive to the turbulence model.

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Section: Flow Solver and Turbulence Modelmentioning

confidence: 99%

CFD Validation for High-Lift Devices: Three-Element Airfoil

Murayama

Zhong

Mukai

et al. 2006

Trans. Japan Soc. Aero. S Sci.

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“…The motivation for our work comes, in part, from the results of Murayama et al [4] who attributed the observed improvement in results predicted for a delta wing experiencing vortex breakdown to improved resolution of the streamwise pressure gradient in the vortex core, and from the observation that there is significant curvature in the velocity field near the surface of maximum tangential velocity [13]. In our approach, we employ vortex characterization, which has been primarily used for visualization applications, to identify regions of the computational domain near the vortex.…”

Section: Approach: Feature-based Mesh Refinementmentioning

confidence: 99%

“…With a somewhat different philosophy, Ito et al [42] employed extent surfaces computed using vortex characterization [7] as a component of a mesh regeneration strategy for the Dacles-Mariani wing [13]. The vortex extent surface was triangulated and used as an embedded surface that was maintained as the volume mesh was generated.…”

Section: Related Workmentioning

confidence: 99%

“…Kim and Rhee [5] computed the solution for the Dacles-Mariani wing [13] on a single-block, structured grid. They employed the second invariant of the rate of deformation tensor as the refinement sensor and studied the effects of various turbulence models.…”

Section: Related Workmentioning

confidence: 99%

“…We demonstrate the efficacy of our approach by applying it to the prediction of the flow fields around two different configurations, a wing in a wind tunnel at 10 • angle of attack [13] and a missile configuration [14] at 0 • angle of attack with canards deflected 15 • spinning at 30 and 60 Hz. We use the wing results to evaluate the effectiveness of different refinement strategies by comparing the numerically predicted results with experimental data [13].…”

Section: Introductionmentioning

confidence: 99%

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Feature‐based adaptive mesh refinement for wingtip vortices

Kasmai

Thompson

Luke

et al. 2011

Numerical Methods in Fluids

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SUMMARYFeature-based solution-adaptive mesh refinement is an attractive strategy when it is known a priori that the resolution of certain key features is critical to achieving the objectives of a simulation. In this paper, we apply vortex characterization techniques, which are typically employed to visualize vortices, to identify regions of the computational domain for mesh refinement. We investigate different refinement strategies that are facilitated by these vortex characterization techniques to simulate the flow past a wing in a wind tunnel. Our results, which we compare with experimental data, indicate that it is necessary to refine the region within and near the vortex extent surface to obtain an accurate prediction. Application of the identified mesh refinement strategy also produced observed improvement in the results predicted for a spinning missile with deflected canards.

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