XFOIL Version 6.94 Calculated polar for: EPPLER 664 (EXTENDED) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 1.1039 0.01535 0.00953 -0.2277 0.6809 0.7380 1.000 1.1674 0.01520 0.00943 -0.2300 0.6734 0.7409 1.500 1.2313 0.01528 0.00950 -0.2323 0.6655 0.7440 2.000 1.2940 0.01510 0.00949 -0.2345 0.6565 0.7467 2.500 1.3574 0.01497 0.00938 -0.2366 0.6464 0.7500 3.000 1.4197 0.01484 0.00940 -0.2385 0.6337 0.7524 3.500 1.4808 0.01461 0.00925 -0.2400 0.6135 0.7548 4.000 1.5395 0.01452 0.00916 -0.2409 0.5769 0.7569 4.500 1.5859 0.01531 0.00950 -0.2392 0.4844 0.7589 5.000 1.6172 0.01752 0.01102 -0.2346 0.3688 0.7609 5.500 1.6440 0.01974 0.01274 -0.2292 0.2789 0.7634 6.000 1.6648 0.02199 0.01462 -0.2225 0.2119 0.7653 6.500 1.6701 0.02447 0.01688 -0.2124 0.1643 0.7671 7.000 1.6781 0.02747 0.01973 -0.2040 0.1261 0.7690 7.500 1.6880 0.03091 0.02306 -0.1973 0.0954 0.7709 8.000 1.6983 0.03480 0.02686 -0.1918 0.0695 0.7734 8.500 1.7096 0.03897 0.03099 -0.1873 0.0486 0.7753 9.000 1.7214 0.04327 0.03529 -0.1833 0.0335 0.7767 9.500 1.7293 0.04802 0.04005 -0.1793 0.0202 0.7788 10.000 1.7317 0.05340 0.04550 -0.1748 0.0111 0.7807 10.500 1.7387 0.05851 0.05078 -0.1713 0.0087 0.7829 11.000 1.7442 0.06395 0.05642 -0.1680 0.0077 0.7851 11.500 1.7500 0.06956 0.06226 -0.1653 0.0072 0.7875 12.000 1.7525 0.07578 0.06871 -0.1628 0.0068 0.7899 12.500 1.7512 0.08266 0.07581 -0.1606 0.0065 0.7924 13.000 1.7444 0.09056 0.08395 -0.1589 0.0063 0.7947 13.500 1.7310 0.09966 0.09330 -0.1578 0.0062 0.7967 14.000 1.7195 0.10885 0.10276 -0.1577 0.0061 0.8001 14.500 1.7097 0.11811 0.11230 -0.1584 0.0060 0.8037 15.000 1.6991 0.12774 0.12221 -0.1600 0.0060 0.8072 15.500 1.6890 0.13753 0.13226 -0.1625 0.0060 0.8107 16.000 1.6806 0.14731 0.14229 -0.1658 0.0059 0.8145 16.500 1.6732 0.15714 0.15239 -0.1700 0.0059 0.8190 17.000 1.6667 0.16693 0.16246 -0.1749 0.0059 0.8248 17.500 1.6606 0.17692 0.17273 -0.1805 0.0059 0.8321 18.000 1.6541 0.18738 0.18349 -0.1871 0.0059 0.8428 18.500 1.6461 0.19842 0.19490 -0.1947 0.0059 0.8709 19.500 1.6237 0.22301 0.22014 -0.2140 0.0060 1.0048 20.000 1.6097 0.23747 0.23490 -0.2263 0.0060 1.0048 20.500 1.5931 0.25372 0.25143 -0.2406 0.0061 1.0048 21.000 1.5733 0.27367 0.27173 -0.2581 0.0063 1.0048