A theoretical basis for extending surface-paneling methods to transonic flow

Erickson, L. L.; Strande, Shawn

doi:10.2514/3.9188

Cited by 24 publications

(2 citation statements)

References 2 publications

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“…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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Section: Introductionmentioning

confidence: 98%

“…In Eqs. (9)(10)(11)(12)(13)(14), the subscripts 1 and 2 refer to the conditions ahead and behind the shock, respectively, while n and t refer to the normal and tangential directions to the shock surface S, respectively, and 9 is the relative direction of the flow behind the shock to that ahead of the shock.…”

Section: Introductionmentioning

confidence: 99%