NACA2415 Family: NACA 4-digit Max thickness: 14.9% at x = 29.94% chord Max camber: 1.7% at x = 40.62% chord Available data sources: JavaFoil+Calcfoil stall+Eppler ext transition Wind Tunnel (UIUC Low-Speed Airfoil Test Program, Vol 2) Wind Tunnel (NACA-TR-824) AeroFoil XFOIL ncrit=9
Notes:
Coordinates generated by JavaFoil Wind tunnel data from NACA TR-824 as digitized by Gregory P.D. Siemens in 1994 at the University of Saskatchewan. The digitized TR-824 data has been processed and interpolated to generate all the plots and can not be guaranteed to be an exact match to the TR-824 plots. Wind tunnel data from the UIUC Low-Speed Airfoil Test Program. The UIUC wind tunnel data is covered by the GNU GPL and the airfoil performance data is copyrighted, and restrictions are placed on its use. The data may be freely copied and used in any way, e.g., for personal use, in magazine articles or with a commercial product. If the data is used in a magazine article or book, the author must reference the appropriate volume of Summary of Low-Speed Airfoil Data and give the address of where it can be obtained. If the data is used in a commercial product, there must be no extra charges for providing it - other than the cost of reproduction and distribution. All products that make use of this data must conspicuously state that it was produced under the UIUC Low-Speed Airfoil Test program, and no restrictions can be placed on the recipient with respect to their use of the source data. Furthermore, they must be allowed to copy the original data and freely distribute it as well. A copy of the license, the copyright notice and the UIUC Low-Speed Airfoil Tests Manifesto (manifest.html) must be included with each distribution of the data.