PAN AIR prediction of NASA Ames 12-foot pressure wind-tunnel interference on a fighter configuration

Snyder, L. D.; Erickson, L. L.

doi:10.2514/6.1984-219

Cited by 3 publications

(2 citation statements)

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“…6 " 15 This type of confidence is desired for any new code, and TranAir is no exception. The reasons for this confidence are 1) an understanding of the well-defined applicability of the code, i.e., linear, irrotational, inviscid flow; and 2) the huge history of successful applications of the code.…”

Section: Tranair: Applicationsmentioning

confidence: 99%

“…6 " 15 A tremendous degree of confidence in the linear-potential solution exists when the code is applied to a problem within the range of applicability of the method. For subsonic cases, the flow is assumed to be inviscid and irrotational, and the perturbation velocities must be small compared to the freestream in order for the solution to be completely valid.…”

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confidence: 99%

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Toward the Routine Aerodynamic Analysis of Complex Configurations

Madson¹,

Erickson²

1990

Applied Computational Aerodynamics

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IntroductionT HE ability to quickly and routinely predict the aerodynamics of complete aircraft configurations is a common goal among designers and engineers. Unfortunately, a trade off has always existed between the generality of the geometry that could be modeled and the level of physics that could be applied to the problem. In general, the more complex the physics that is modeled, the simpler the geometry needs to be to generate a suitable surface-conforming flowfield grid. Although Navier-Stokes and Euler codes are able to handle increasingly complex geometries because of improvements in the grid-generation process, they are still not able to model truly complete configurations in a routine manner. Each new geometry demands a substantial amount of calendar time in the generation of the flowfield grid, and there is the need to "tweak" various parameters within the codes themselves in order to adjust them for each new geometry and flow condition. If an analysis of a series of candidate configurations is desired, each new configuration requires a newly defined flowfield grid.The ability to quickly model and analyze a configuration is of great importance to the engineer, who is often met with very restrictive time constraints when asked to provide a prediction of the aerodynamics of a new configuration, or to calculate the effect of adding or removing a piece of geometry from an existing model. For many cases it is not necessary to model the complete physics of the problem in order to obtain a solution that provides important insight into the design of a particular configuration.Linear-potential panel methods have been able to model arbitrary geometries for many years. One of these codes, PanAir, 1 ' 5 is able to predict supersonic as well as subsonic results about these general geometries. Unfortunately, the simplifications of the actual physics necessary to run 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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Section: Tranair: Applicationsmentioning

confidence: 99%

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confidence: 99%