Calculation of Unsteady Transonic Flow Over an Airfoil

Chyu, W. J.; Davis, Sanford S.; Chang, Keun Sick

doi:10.2514/6.1979-1554

Cited by 7 publications

(9 citation statements)

References 6 publications

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“…Figure 10 shows the key result-a history of lift coe cient C l versus angle of attack . Comparison with experimental data is very good, and consistent with inviscid calculations reported in References [46,47]. In addition, in References [46,47] only minor improvements were shown for viscous calculations.…”

Section: 21supporting

confidence: 84%

MPDATA error estimator for mesh adaptivity

Szmelter

Smolarkiewicz

2005

Numerical Methods in Fluids

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SUMMARYIn multidimensional positive deÿnite advection transport algorithm (MPDATA) the leading error as well as the ÿrst-and second-order solutions are known explicitly by design. This property is employed to construct reÿnement indicators for mesh adaptivity. Recent progress with the edge-based formulation of MPDATA facilitates the use of the method in an unstructured-mesh environment. In particular, the edge-based data structure allows for ow solvers to operate on arbitrary hybrid meshes, thereby lending itself to implementations of various mesh adaptivity techniques. A novel unstructured-mesh nonoscillatory forward-in-time (NFT) solver for compressible Euler equations is used to illustrate the beneÿts of adaptive remeshing as well as mesh movement and enrichment for the e cacy of MPDATAbased ow solvers. Validation against benchmark test cases demonstrates robustness and accuracy of the approach.

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Section: 21supporting

confidence: 84%

MPDATA error estimator for mesh adaptivity

Szmelter

Smolarkiewicz

2005

Numerical Methods in Fluids

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“…Presented as Paper 85-1514 at the AIAA 7th Computational Fluid Dynamics Conference, Cincinnati, OH, July 15-17, 1985;received Nov. 25, 1986; revision received Dec. 9,1987. Copyright © American Institute of Aeronautics and Astronautics, Inc., 1988.…”

Section: Introductionmentioning

confidence: 99%

“…Sides 6 used the implicit method of Lerat, Sides, and Daru 7 to compute unsteady flows past moving airfoils. Steger 8 and Chyu et al 9 used implicit finite difference algorithms. There is, however, considerable scope for improvement in the solution of Euler equations for flows past moving airfoils, especially in the areas of computational speed, artificial dissipation, and the treatment of the boundary conditions.…”

Section: Introductionmentioning

confidence: 99%

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Computation of unsteady transonic flows by the solution of Euler equations

Venkatakrishnan

Jameson

1988

AIAA Journal

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Transonic flow over an airfoil in motion has been computed by solving the Euler equations using two methods. The finite volume scheme is used to spatially discretize the integral form of the Euler equations for a moving domain. The first method uses dissipative terms constructed according to the theory of total variation diminishing (or TVD) schemes. The TVD scheme is presented in a semidiscrete form for a scalar conservation law and then is formally extended to a system of conservation laws. The resulting system of ordinary differential equations is integrated in time by a multistage scheme. A new class of multistage schemes that preserve the TVD property is used. The technique of residual averaging, which permits the use of larger time steps, is extended to unsteady problems in a form that preserves time accuracy. The second method utilizes dissipative terms constructed from second and fourth differences in the dependent variables. Nonreflecting boundary conditions are used in the far field, allowing the use of a moving mesh.Downloaded by UNIVERSITY OF CALIFORNIA -DAVIS on February 4, 2015 | http://arc.aiaa.org |

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“…9 are the experimentally measured pressure distributions taken from Ref. [ 11 ]. The comparison between the computational and experimental results show that the agreement is fair.…”

Section: Numerical Resultsmentioning

confidence: 90%

Variable-domain variational finite element solution of IA inverse problem of 2-D unsteady compressible flow around oscillating airfoils

Guo

Liu

1999

J. of Shanghai Univ.

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Al~traet In this paper, on the basis of the variational principles developed the finite element method (FEM) is employed for numerical solution of the inverse pro blem of 2-D unsteady compressible flow around oscillating airfoils by incorporating the non-reflecting far-field boundary conditions and a new unsteady Kutta condition. All unknown boundary (airfoil contour) and discontinuities(shocks and free trailing vortex sheets) are determined v/a the functional variation with variable domain and artificial density concept. For the numerical realization of the variable-domain variation, a special finite element with self-adjusting nodes is also suggested herein. The numerical results show that the present method is effective for the design of unsteady airfoil.

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Calculation of Unsteady Transonic Flow Over an Airfoil

Cited by 7 publications

References 6 publications

MPDATA error estimator for mesh adaptivity

MPDATA error estimator for mesh adaptivity

Computation of unsteady transonic flows by the solution of Euler equations

Variable-domain variational finite element solution of IA inverse problem of 2-D unsteady compressible flow around oscillating airfoils

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