Computation of transonic vortex flows past delta wings Integral equation approach

Kandil, Osama A.; Yates, E. C.

doi:10.2514/6.1985-1582

Cited by 26 publications

(4 citation statements)

References 11 publications

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“…These results confirm the observation by Vorropoulos and Wendt 2 and previous calculations using the integral equation approach. 6 This case is indicated as In Fig. 6, we show the results for a flat-plate sharp-edged delta wing with a grid size of 64 X 64 for M^ = 2.4 and a == 19 deg.…”

Section: Computational Resultsmentioning

confidence: 99%

Influence of numerical dissipation on computational Euler equations for vortex-dominated flows

Kandil

Chuang

1987

AIAA Journal

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Steady, supersonic vortex-dominated flows are solved using the unsteady Euler equations for conical flows around sharp-and round-edged delta wings. A finite-volume scheme with a four-stage Runge-Kutta time stepping and explicit second-and fourth-order dissipation terms has been developed to obtain the steady flow solution through psuedo time stepping. The grid is generated by using a modified Joukowski transformation. The scheme has been applied to flat-plate and elliptic-section delta wings at different angles of attack, freestream Mach numbers, and grid sizes. For the sharp-edged wings, separated-flow solutions are always obtained, while for round-edged wings both separated-and attached-flow solutions can be obtained, depending on the level of numerical dissipation. The round-edged results also show that the solutions are independent of the way time stepping is done-local time stepping and global minimum time stepping produce the same solutions.

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Section: Computational Resultsmentioning

confidence: 99%

Influence of numerical dissipation on computational Euler equations for vortex-dominated flows

Kandil

Chuang

1987

AIAA Journal

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“…It is a two-dimensional application of the shock-capturing scheme by Kandil and Yates. 12 Shock panels are then introduced at the shock location, the fourth integral term of Eq. (8) is now taken into account, Eqs.…”

Section: Shock Capturing-shock Fitting Schemementioning

confidence: 99%

“…Piers and Sloof 10 and Tseng and Morino 11 have developed IE schemes for the TSP equation, while Kandil and Yates, 12 Oskam, 13 Erickson and Strande, 14 Sinclair, 15 and Kandil and Hu 16 have developed IE schemes for the FP equation. Since the potential equation cannot accurately treat flows with strong shocks, the IE schemes for the FP equation must be modified to accurately treat flows with strong shocks.…”

Section: Introductionmentioning

confidence: 98%

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Full-potential integral solution for transonic flows with and without embedded Euler domains

Kandil

1988

AIAA Journal

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Two methods are presented to solve transonic airfoil flow problems. The first method is based on the integral equation solution of the full-potential equation in terms of the velocity field. A shock capturing-shock fitting scheme has been developed. In the shock-fitting part of the scheme, shock panels are introduced at the shock location. The shock panels are fitted by using the Rankine-Hugoniot relations. The second method is a coupling of the integral solution of the full-potential equation with the pseudotime integration of Euler equations, which are used in a small embedded region around the shock. This scheme is caUed the integral equation-embedded Euler scheme. The two methods are applied to NACA 0012 and 64A010A airfoils over a wide range of Mach numbers, and the results are in good agreement with the experimental data and other computational results. The schemes converge within a number of iterations that is one order of magnitude less than the finite-difference schemes.

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Structural Optimization

MacBain¹,

Spillers²

1975

CISM International Centre for Mechanical Sciences

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In this paper we propose a new approach for constructing efficient schemes for non-smooth convex optimization. It is based on a special smoothing technique, which can be applied to functions with explicit max-structure. Our approach can be considered as an alternative to black-box minimization. From the viewpoint of efficiency estimates, we manage to improve the traditional bounds on the number of iterations of the gradient schemes from O 1 2 to O 1 , keeping basically the complexity of each iteration unchanged.

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Computation of transonic vortex flows past delta wings Integral equation approach

Cited by 26 publications

References 11 publications

Influence of numerical dissipation on computational Euler equations for vortex-dominated flows

Influence of numerical dissipation on computational Euler equations for vortex-dominated flows

Full-potential integral solution for transonic flows with and without embedded Euler domains

Structural Optimization

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