A two-step grid redistribution method

Tang, Lei; Baeder, James D.

doi:10.1016/s0045-7930(01)00092-5

Cited by 4 publications

(9 citation statements)

References 14 publications

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“…The C-grid in Figure 1 is used as the baseline grid for the computation. The two-step grid redistribution method of Reference [19] is used to locally refine the mesh in the vortex region. The computation starts with the calculation of the steady solution around the NACA0012 airfoil.…”

Section: Subcritical Head-on Interactionmentioning

confidence: 99%

“…The measured time histories of the surface pressure coefficient at three chordwise locations (2, 5, and 10% of the chord length) in Reference [20] are used to verify the reduced numerical diffusion contained in the direct numerical simulation by combining the two-step grid redistribution method of Reference [19] and the improved spatially third-order accurate Euler solver of Reference [14]. It is found in Figure 5 that compared with multiblock grid Navier-Stokes results in Reference [20] based on nearly 193 000 points, our adaptive Euler computation with only about 32 800 points gives much steeper slopes of the pressure and much larger peak values due to much less numerical diffusion inherent in the computation.…”

Section: Subcritical Head-on Interactionmentioning

confidence: 99%

“…This can be observed in both the magnitude of the negative peak loading as well as the slope of the loading as the vortex passes underneath the airfoil. The combination of the grid redistribution method of Reference [19] and the improved Euler solver of Reference [14] significantly improves the result. In fact, the result from the direct Euler simulation using the modified TURNS methodology is almost identical to the one given by the perturbation method.…”

Section: Supercritical Airfoil-vortex Interactionmentioning

confidence: 99%

“…This happens even when the grid redistribution is already turned off. To implement grid redistribution for improving acoustic wave capturing, one needs to use density gradient instead of the modified point attraction function of (1) to determine the length scale l in the grid redistribution method of Reference [19].…”

Section: Supercritical Airfoil-vortex Interactionmentioning

confidence: 99%

“…However, it is a common experience that the predicted vortex structure is diffused very rapidly as the vortex convects in the flowfield due to large numerical diffusion contained in upwind shock-capturing schemes and have no grid points or only one or two across the vortex core. In order to accurately capture or preserve this vortex structure, the two-step grid redistribution method of Reference [19] will be used to locally refine this grid in the vortex region.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive Euler simulations of airfoil–vortex interaction

Tang

Baeder

2006

Numerical Methods in Fluids

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SUMMARYA grid redistribution method is used together with an improved spatially third-order accurate Euler solver to improve the accuracy of direct Euler simulations of airfoil-vortex interaction. The presented numerical results of two airfoil-vortex interaction cases indicate that with combination of the two methods, the numerical diffusion of vorticity inherent in the direct Euler simulations is drastically reduced without increasing the number of grid points. With some extra works due to grid redistribution, the predicted vortex structure is well preserved after a long convection and much sharper acoustic wave front resulting from airfoil-vortex interaction is captured.

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Section: Subcritical Head-on Interactionmentioning

confidence: 99%

Section: Subcritical Head-on Interactionmentioning

confidence: 99%

Section: Supercritical Airfoil-vortex Interactionmentioning

confidence: 99%

Section: Supercritical Airfoil-vortex Interactionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Adaptive Euler simulations of airfoil–vortex interaction

Tang

Baeder

2006

Numerical Methods in Fluids

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Adaptive Euler Simulation of Supercritical Interaction of Airfoil and Vortex

Tang

Baeder

2003

16th AIAA Computational Fluid Dynamics Conference

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2D and 3D gust response using a prescribed velocity method in viscous flows

Huntley¹,

Jones²,

Gaitonde³

2016

46th AIAA Fluid Dynamics Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms 2D and 3D gust response using a prescribed velocity method in viscous flows Results are presented for the interaction between a wide body aircraft and a gust using the split velocity method, which has been extended to viscous flows. The method is first demonstrated for two dimensions on a NACA 0012 aerofoil before being extended to the 3D case. In both instances a series of 1-Cosine gusts were used to compare solutions between the split velocity method and, another prescribed velocity method, the field velocity method. The field velocity method is shown to be a simplification of the split velocity method, with the latter requiring extra source terms that account for the interaction of the aerofoil on the gust. It was found that the differences were small for longer wavelength gusts but at shorter wavelengths the gradients become larger and the split velocity method produces more accurate results.

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A two-step grid redistribution method

Cited by 4 publications

References 14 publications

Adaptive Euler simulations of airfoil–vortex interaction

Adaptive Euler simulations of airfoil–vortex interaction

Adaptive Euler Simulation of Supercritical Interaction of Airfoil and Vortex

2D and 3D gust response using a prescribed velocity method in viscous flows

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