Numerical simulation of transonic separated flows over low-aspect-ratio wings

Kaẏnak, Ünver; Holst, Terry L.; Sorenson, Reese L.; Cantwell, Brian

doi:10.2514/3.45472

Cited by 6 publications

(3 citation statements)

References 17 publications

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“…Comparison of experimental and computed pressure coefficients for wing C; M^ = 0.82, a = 5 deg, /te mac = 6.8 x 10 6 (taken from Kaynak et al32 ).…”

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confidence: 99%

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Navier-Stokes Computations About Complex Configurations Including a Complete F-16 Aircraft

Holst

Flores²,

Chaderjian³

et al. 1990

Applied Computational Aerodynamics

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IntroductionC OMPUTATIONAL fluid dynamics (CFD) algorithm and computer hardware developments have been rapidly advancing over the last decade. CFD computer codes have been used in many applications to improve the design of aircraft. For example, linear panel methods have been used to improve the design of complex aircraft configurations providing the flow does not contain shock waves or significant separation. Nonlinear potential methods have been used to remove the adverse characteristics caused by shock waves in the transonic regime with the limitation that vorticity and entropy production are not large. The problem of solving the Euler/Navier-Stokes equations about reasonably complete aircraft configurations is now the central issue facing the CFD research community, and, in fact, many significant results demonstrating the power of this approach have already been produced.There are many reasons for pursuing this line of research. First, the large computer costs associated with the numerical solution of the Euler/Navier-Stokes equations in three dimensions is rapidly decreasing. This is a direct result of new improved algorithms and fast vector computers such as the Cray XMP and YMP, the Cray 2, and the CDC Cyber 205. Second, there Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org |

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“…Comparison of experimental and computed pressure coefficients for wing C; M^ = 0.82, a = 5 deg, /te mac = 6.8 x 10 6 (taken from Kaynak et al32 ).…”

mentioning

confidence: 99%

“… 22. Mach number contours just above the boundary layer on the upper surface of wing C; M^ = 0.90, a = 5 deg, Re msic = 6.8 x 10 6 (taken from Kaynak et al32 ).…”

mentioning

confidence: 99%

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Navier-Stokes Computations About Complex Configurations Including a Complete F-16 Aircraft

Holst

Flores²,

Chaderjian³

et al. 1990

Applied Computational Aerodynamics

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A general classification of three-dimensional flow fields

Chong

Perry

Cantwell

1990

Physics of Fluids A: Fluid Dynamics

1,616

1,043

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The geometry of solution trajectories for three first-order coupled linear differential equations can be related and classified using three matrix invariants. This provides a generalized approach to the classification of elementary three-dimensional flow patterns defined by instantaneous streamlines for flow at and away from no-slip boundaries for both compressible and incompressible flow. Although the attention of this paper is on the velocity field and its associated deformation tensor, the results are valid for any smooth three-dimensional vector field. For example, there may be situations where it is appropriate to work in terms of the vorticity field or pressure gradient field. In any case, it is expected that the results presented here will be of use in the interpretation of complex flow field data.

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