XFOIL Version 6.96 Calculated polar for: EPPLER 580 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.2820 0.08641 0.08473 -0.0876 0.9867 0.0160 -11.000 -0.3596 0.05739 0.05543 -0.1121 0.9845 0.0159 -10.750 -0.3807 0.05021 0.04807 -0.1189 0.9791 0.0160 -10.500 -0.3797 0.04583 0.04358 -0.1246 0.9754 0.0161 -10.250 -0.3762 0.04100 0.03855 -0.1318 0.9727 0.0162 -9.250 -0.3563 0.02353 0.01954 -0.1430 0.9462 0.0156 -9.000 -0.3409 0.02238 0.01819 -0.1416 0.9366 0.0154 -8.750 -0.3072 0.02103 0.01669 -0.1440 0.9333 0.0153 -8.500 -0.2809 0.01981 0.01534 -0.1447 0.9256 0.0152 -8.250 -0.2468 0.01863 0.01403 -0.1468 0.9198 0.0151 -8.000 -0.2165 0.01747 0.01274 -0.1481 0.9112 0.0151 -7.750 -0.1842 0.01625 0.01140 -0.1496 0.9025 0.0151 -7.500 -0.1559 0.01542 0.01046 -0.1502 0.8911 0.0151 -7.250 -0.1307 0.01431 0.00925 -0.1501 0.8788 0.0151 -7.000 -0.1079 0.01321 0.00806 -0.1497 0.8662 0.0154 -6.750 -0.0848 0.01240 0.00718 -0.1494 0.8538 0.0158 -6.500 -0.0604 0.01184 0.00655 -0.1493 0.8417 0.0161 -6.250 -0.0357 0.01138 0.00602 -0.1492 0.8296 0.0164 -6.000 -0.0103 0.01098 0.00555 -0.1491 0.8179 0.0169 -5.750 0.0157 0.01062 0.00512 -0.1492 0.8069 0.0173 -5.500 0.0420 0.01031 0.00472 -0.1493 0.7960 0.0177 -5.250 0.0688 0.01002 0.00436 -0.1494 0.7849 0.0181 -5.000 0.0959 0.00976 0.00403 -0.1495 0.7746 0.0186 -4.750 0.1231 0.00954 0.00373 -0.1497 0.7644 0.0189 -4.500 0.1506 0.00935 0.00347 -0.1498 0.7540 0.0193 -4.250 0.1785 0.00907 0.00311 -0.1501 0.7442 0.0203 -4.000 0.2062 0.00890 0.00286 -0.1503 0.7345 0.0221 -3.750 0.2343 0.00876 0.00268 -0.1505 0.7248 0.0237 -3.500 0.2623 0.00864 0.00251 -0.1507 0.7158 0.0274 -3.250 0.2920 0.00810 0.00224 -0.1518 0.7064 0.1114 -3.000 0.3254 0.00680 0.00176 -0.1546 0.6978 0.3751 -2.750 0.3546 0.00654 0.00174 -0.1553 0.6889 0.4743 -2.500 0.3832 0.00656 0.00175 -0.1555 0.6806 0.4982 -2.250 0.4109 0.00665 0.00180 -0.1555 0.6723 0.5155 -2.000 0.4394 0.00675 0.00186 -0.1556 0.6643 0.5300 -1.750 0.4669 0.00691 0.00199 -0.1555 0.6564 0.5436 -1.500 0.4952 0.00696 0.00202 -0.1556 0.6487 0.5498 -1.250 0.5226 0.00708 0.00208 -0.1555 0.6412 0.5547 -1.000 0.5510 0.00715 0.00212 -0.1556 0.6340 0.5593 -0.750 0.5786 0.00725 0.00214 -0.1556 0.6267 0.5612 -0.500 0.6068 0.00725 0.00213 -0.1558 0.6201 0.5636 -0.250 0.6345 0.00730 0.00214 -0.1558 0.6131 0.5656 0.000 0.6623 0.00736 0.00218 -0.1559 0.6067 0.5677 0.250 0.6902 0.00741 0.00221 -0.1559 0.6000 0.5697 0.500 0.7175 0.00750 0.00225 -0.1559 0.5936 0.5717 0.750 0.7456 0.00755 0.00228 -0.1560 0.5873 0.5736 1.000 0.7729 0.00764 0.00233 -0.1560 0.5808 0.5756 1.250 0.8007 0.00771 0.00238 -0.1560 0.5747 0.5772 1.500 0.8281 0.00775 0.00241 -0.1561 0.5682 0.5795 1.750 0.8551 0.00783 0.00247 -0.1560 0.5620 0.5815 2.000 0.8828 0.00788 0.00253 -0.1560 0.5558 0.5834 2.250 0.9094 0.00799 0.00262 -0.1559 0.5491 0.5856 2.500 0.9369 0.00806 0.00269 -0.1559 0.5430 0.5877 2.750 0.9636 0.00816 0.00276 -0.1558 0.5360 0.5899 3.000 0.9904 0.00826 0.00285 -0.1556 0.5295 0.5918 3.250 1.0172 0.00835 0.00293 -0.1556 0.5225 0.5933 3.500 1.0432 0.00845 0.00302 -0.1553 0.5155 0.5959 3.750 1.0700 0.00852 0.00312 -0.1552 0.5081 0.5983 4.000 1.0954 0.00866 0.00324 -0.1549 0.5004 0.6006 4.250 1.1218 0.00875 0.00335 -0.1547 0.4922 0.6029 4.500 1.1469 0.00890 0.00347 -0.1543 0.4836 0.6051 4.750 1.1723 0.00903 0.00360 -0.1539 0.4745 0.6073 5.000 1.1974 0.00918 0.00373 -0.1535 0.4655 0.6092 5.500 1.2461 0.00948 0.00404 -0.1524 0.4450 0.6148 5.750 1.2696 0.00966 0.00421 -0.1518 0.4347 0.6175 6.000 1.2916 0.00987 0.00440 -0.1507 0.4232 0.6201 6.250 1.3136 0.01007 0.00458 -0.1498 0.4116 0.6227 6.500 1.3353 0.01029 0.00478 -0.1487 0.3999 0.6250 6.750 1.3562 0.01053 0.00501 -0.1475 0.3870 0.6281 7.000 1.3764 0.01081 0.00527 -0.1463 0.3732 0.6312 7.250 1.3959 0.01114 0.00555 -0.1449 0.3570 0.6346 7.500 1.4142 0.01153 0.00588 -0.1433 0.3389 0.6380 7.750 1.4315 0.01195 0.00623 -0.1416 0.3208 0.6410 8.000 1.4483 0.01240 0.00662 -0.1398 0.3017 0.6447 8.250 1.4650 0.01287 0.00702 -0.1380 0.2822 0.6484 8.500 1.4801 0.01339 0.00748 -0.1360 0.2631 0.6524 8.750 1.4937 0.01400 0.00799 -0.1338 0.2436 0.6562 9.000 1.5072 0.01461 0.00854 -0.1316 0.2230 0.6605 9.250 1.5188 0.01531 0.00917 -0.1292 0.2030 0.6652 9.500 1.5295 0.01608 0.00985 -0.1267 0.1840 0.6703 9.750 1.5394 0.01689 0.01059 -0.1241 0.1645 0.6756 10.000 1.5488 0.01775 0.01140 -0.1215 0.1478 0.6817 10.250 1.5566 0.01872 0.01230 -0.1188 0.1312 0.6879 10.500 1.5640 0.01975 0.01328 -0.1162 0.1154 0.6947 10.750 1.5713 0.02082 0.01431 -0.1137 0.1017 0.7024 11.000 1.5780 0.02197 0.01544 -0.1112 0.0891 0.7107 11.250 1.5827 0.02330 0.01673 -0.1087 0.0755 0.7203 11.500 1.5867 0.02473 0.01814 -0.1062 0.0633 0.7314 11.750 1.5905 0.02626 0.01967 -0.1039 0.0527 0.7443 12.000 1.5914 0.02806 0.02146 -0.1015 0.0413 0.7600 12.250 1.5903 0.03012 0.02352 -0.0991 0.0310 0.7797 12.500 1.5886 0.03233 0.02577 -0.0969 0.0211 0.8067 12.750 1.5838 0.03483 0.02836 -0.0946 0.0123 0.8551 13.000 1.5807 0.03681 0.03053 -0.0921 0.0094 1.0000 13.250 1.5846 0.03892 0.03269 -0.0910 0.0082 1.0000 13.500 1.5885 0.04110 0.03493 -0.0899 0.0076 1.0000 13.750 1.5907 0.04353 0.03742 -0.0890 0.0070 1.0000 14.000 1.5943 0.04588 0.03986 -0.0882 0.0067 1.0000 14.250 1.5986 0.04825 0.04230 -0.0876 0.0065 1.0000 14.500 1.6018 0.05079 0.04492 -0.0871 0.0063 1.0000 14.750 1.6041 0.05350 0.04771 -0.0866 0.0061 1.0000 15.000 1.6058 0.05636 0.05064 -0.0863 0.0059 1.0000 15.250 1.6065 0.05942 0.05379 -0.0862 0.0058 1.0000 15.500 1.6063 0.06266 0.05712 -0.0861 0.0056 1.0000 15.750 1.6052 0.06611 0.06065 -0.0862 0.0055 1.0000 16.000 1.6028 0.06981 0.06444 -0.0864 0.0054 1.0000 16.250 1.5988 0.07383 0.06856 -0.0868 0.0053 1.0000 16.500 1.5935 0.07815 0.07299 -0.0874 0.0051 1.0000 16.750 1.5865 0.08283 0.07778 -0.0882 0.0051 1.0000 17.000 1.5771 0.08796 0.08305 -0.0893 0.0050 1.0000