![]() ![]() This document may accidentally refer to trade names and trademarks, which are owned by national or international companies, but which are unknown by me. Of the given material is not allowed, if the resulting product is sold for more If you use thisĭocument for a publication, you have to cite the source. You may use the data given in this document for your personal use. I cannot takeĪny responsibility for actions you perform based on data, assumptions, calculations This is a privately owned, non-profit page of purely educational purpose.Īny statements may be incorrect and unsuitable for practical usage. Me a copy of your e-mail after a month or so. If you have not lost patience, you might want to send It might take some time until you receive an answerĪnd in some cases you may even receive no answer at all. Page] Suggestions? Corrections? Remarks? e-mail:ĭue to the increasing amount of SPAM mail, I have ![]() Velocity distribution shows large gradients. To 120) and that the points must be distributed more dense in regions where the ![]() This example shows, that you should use enough points (at least 50, better 80 TheĪnalysis shows a closer agreement with the experiments, but maximum lift is Spaced" coordinate set with a finer resolution at the trailing edge. Then the coordinates were re-splined to only 53 points This created the first curve with higherĭrag coefficients. The first analysis used the given 51 points, which were defined near The coordinates for this airfoil were imported from the Wiechers/BenderĬoordinate database and the analysis was performed for two cases, using a smooth The airfoil coordinates were created with JavaFoil, Here we see a similar result with the analysis quite close to theĮxperimental data. Lower lift coefficients, the lower surface becomes fully turbulent and the drag The drag coefficient lies close to theĮxperimental values but is considerably higher than the XFLR5 prediction. While these are modeled in XFLR5, the deviation from theĮxperimental values is also rather large. (dCl/dalfa) is also overpredicted because no boundary layer displacement effectsĪre modeled. Over-predicted by both numerical methods (JavaFoil, XFLR5). Wind tunnel tests performed in the Laminar Wind Tunnel at Stuttgart, The data This classic airfoil has been analyzed with JavaFoil and compared against Institute of Aero- and Gas-Dynamics of the University of Stuttgart are shown Some comparisons between Experiments at the laminar wind tunnel of the It isĪlways a good idea to perform some tests of your own before you start complexĭevelopment work with a computer program like JavaFoil or the like. Results can be expected and the results should be used with thought. Thus deviations between experiments and JavaFoil Like all mathematical models, the procedures combined in JavaFoil can ![]()
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