XFOIL Version 6.96 Calculated polar for: EPPLER 417 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.4667 0.07375 0.07185 -0.1032 0.9796 0.0116 -12.000 -0.5058 0.06273 0.06061 -0.1112 0.9777 0.0115 -11.750 -0.5252 0.05615 0.05384 -0.1163 0.9763 0.0114 -11.500 -0.5285 0.05223 0.04981 -0.1199 0.9753 0.0116 -11.250 -0.5333 0.04812 0.04555 -0.1235 0.9743 0.0117 -11.000 -0.5523 0.04575 0.04308 -0.1208 0.9691 0.0117 -10.750 -0.5606 0.04251 0.03968 -0.1215 0.9658 0.0118 -10.500 -0.5586 0.04011 0.03714 -0.1230 0.9637 0.0121 -10.250 -0.5567 0.03725 0.03408 -0.1245 0.9619 0.0124 -9.000 -0.5124 0.02299 0.01823 -0.1205 0.9491 0.0110 -8.750 -0.5172 0.02267 0.01784 -0.1147 0.9426 0.0109 -8.500 -0.4937 0.02192 0.01700 -0.1147 0.9409 0.0108 -8.250 -0.4683 0.02090 0.01589 -0.1150 0.9398 0.0107 -8.000 -0.4416 0.02008 0.01500 -0.1154 0.9389 0.0106 -7.750 -0.4174 0.01859 0.01345 -0.1152 0.9382 0.0108 -7.500 -0.3916 0.01746 0.01227 -0.1155 0.9376 0.0108 -7.250 -0.3638 0.01652 0.01130 -0.1163 0.9370 0.0108 -7.000 -0.3357 0.01543 0.01016 -0.1175 0.9364 0.0110 -6.750 -0.3061 0.01434 0.00904 -0.1193 0.9360 0.0116 -6.500 -0.2739 0.01367 0.00834 -0.1212 0.9356 0.0121 -6.250 -0.2749 0.01354 0.00817 -0.1158 0.9284 0.0122 -6.000 -0.2455 0.01304 0.00764 -0.1169 0.9271 0.0128 -5.750 -0.2140 0.01257 0.00714 -0.1183 0.9263 0.0132 -5.500 -0.1813 0.01213 0.00666 -0.1199 0.9256 0.0136 -5.250 -0.1480 0.01175 0.00624 -0.1215 0.9251 0.0141 -5.000 -0.1138 0.01131 0.00576 -0.1234 0.9247 0.0154 -4.750 -0.0791 0.01094 0.00537 -0.1253 0.9244 0.0176 -4.500 -0.0437 0.01056 0.00501 -0.1274 0.9241 0.0261 -4.250 -0.0014 0.00891 0.00424 -0.1328 0.9241 0.2461 -4.000 0.0416 0.00759 0.00370 -0.1379 0.9242 0.4651 -3.750 0.0792 0.00732 0.00357 -0.1404 0.9239 0.5217 -3.500 0.1163 0.00719 0.00348 -0.1425 0.9235 0.5461 -3.250 0.1528 0.00709 0.00337 -0.1445 0.9230 0.5591 -3.000 0.1897 0.00705 0.00334 -0.1465 0.9224 0.5762 -2.750 0.2267 0.00699 0.00326 -0.1486 0.9218 0.5854 -2.500 0.2635 0.00694 0.00320 -0.1506 0.9210 0.5906 -2.250 0.2747 0.00702 0.00326 -0.1470 0.9151 0.5945 -2.000 0.3073 0.00690 0.00312 -0.1481 0.9130 0.5974 -1.750 0.3426 0.00674 0.00297 -0.1498 0.9115 0.6001 -1.500 0.3801 0.00658 0.00280 -0.1519 0.9099 0.6025 -1.250 0.4180 0.00643 0.00264 -0.1542 0.9082 0.6049 -1.000 0.4456 0.00640 0.00261 -0.1542 0.9050 0.6074 -0.750 0.4696 0.00638 0.00259 -0.1534 0.9010 0.6097 -0.500 0.5007 0.00633 0.00252 -0.1542 0.8983 0.6116 -0.250 0.5345 0.00620 0.00241 -0.1556 0.8957 0.6140 0.000 0.5680 0.00609 0.00231 -0.1569 0.8920 0.6162 0.250 0.5894 0.00605 0.00229 -0.1555 0.8850 0.6182 0.500 0.6216 0.00597 0.00221 -0.1564 0.8807 0.6204 0.750 0.6473 0.00595 0.00221 -0.1560 0.8746 0.6227 1.000 0.6748 0.00591 0.00216 -0.1559 0.8677 0.6248 1.250 0.7010 0.00590 0.00215 -0.1556 0.8594 0.6265 1.500 0.7308 0.00584 0.00209 -0.1561 0.8498 0.6288 1.750 0.7562 0.00583 0.00209 -0.1555 0.8376 0.6309 2.000 0.7822 0.00586 0.00210 -0.1551 0.8223 0.6329 2.250 0.8057 0.00593 0.00213 -0.1542 0.8007 0.6349 2.500 0.8269 0.00609 0.00217 -0.1527 0.7690 0.6369 2.750 0.8410 0.00636 0.00227 -0.1496 0.7277 0.6391 3.000 0.8452 0.00680 0.00244 -0.1445 0.6732 0.6410 3.250 0.8504 0.00733 0.00270 -0.1397 0.6143 0.6429 3.500 0.8570 0.00796 0.00302 -0.1354 0.5437 0.6451 3.750 0.8697 0.00853 0.00334 -0.1325 0.4841 0.6470 4.000 0.8848 0.00911 0.00365 -0.1301 0.4252 0.6489 4.250 0.9013 0.00970 0.00398 -0.1281 0.3665 0.6510 4.500 0.9203 0.01021 0.00428 -0.1266 0.3202 0.6532 4.750 0.9384 0.01079 0.00462 -0.1250 0.2673 0.6552 5.000 0.9566 0.01140 0.00498 -0.1234 0.2185 0.6570 5.250 0.9748 0.01201 0.00536 -0.1219 0.1692 0.6590 5.500 0.9926 0.01266 0.00579 -0.1203 0.1228 0.6610 5.750 1.0097 0.01340 0.00628 -0.1186 0.0759 0.6630 6.000 1.0240 0.01441 0.00696 -0.1164 0.0233 0.6651 6.250 1.0441 0.01494 0.00744 -0.1151 0.0139 0.6673 6.500 1.0653 0.01538 0.00791 -0.1140 0.0120 0.6694 6.750 1.0869 0.01578 0.00834 -0.1130 0.0113 0.6714 7.000 1.1077 0.01623 0.00884 -0.1119 0.0106 0.6731 7.250 1.1282 0.01668 0.00935 -0.1108 0.0101 0.6754 7.500 1.1472 0.01727 0.00999 -0.1094 0.0095 0.6776 7.750 1.1633 0.01812 0.01095 -0.1074 0.0089 0.6798 8.000 1.1818 0.01872 0.01160 -0.1060 0.0088 0.6821 8.250 1.2001 0.01930 0.01225 -0.1045 0.0086 0.6843 8.500 1.2174 0.01998 0.01298 -0.1029 0.0085 0.6864 8.750 1.2340 0.02070 0.01377 -0.1012 0.0083 0.6882 9.000 1.2501 0.02143 0.01458 -0.0995 0.0082 0.6907 9.250 1.2648 0.02227 0.01550 -0.0976 0.0081 0.6929 9.500 1.2797 0.02311 0.01642 -0.0957 0.0079 0.6953 9.750 1.2933 0.02405 0.01745 -0.0937 0.0078 0.6978 10.000 1.3067 0.02500 0.01847 -0.0918 0.0076 0.7001 10.250 1.3191 0.02609 0.01963 -0.0897 0.0074 0.7022 10.500 1.3315 0.02716 0.02078 -0.0878 0.0073 0.7046 10.750 1.3433 0.02830 0.02201 -0.0858 0.0071 0.7070 11.000 1.3542 0.02956 0.02335 -0.0837 0.0070 0.7093 11.250 1.3638 0.03096 0.02483 -0.0816 0.0068 0.7118 11.500 1.3727 0.03252 0.02649 -0.0795 0.0067 0.7144 11.750 1.3804 0.03433 0.02839 -0.0774 0.0066 0.7168 12.000 1.3883 0.03635 0.03053 -0.0754 0.0066 0.7191 12.250 1.3954 0.03882 0.03315 -0.0735 0.0065 0.7215 12.500 1.4009 0.04266 0.03724 -0.0716 0.0063 0.7235 12.750 1.4022 0.04441 0.03915 -0.0692 0.0063 0.7261 13.000 1.4038 0.04652 0.04142 -0.0671 0.0062 0.7287 13.250 1.4036 0.04903 0.04409 -0.0651 0.0062 0.7312 13.500 1.4013 0.05179 0.04702 -0.0632 0.0062 0.7335 13.750 1.3964 0.05501 0.05044 -0.0615 0.0062 0.7362 14.000 1.3895 0.05848 0.05410 -0.0600 0.0062 0.7388 14.250 1.3799 0.06246 0.05828 -0.0588 0.0062 0.7413 14.500 1.3697 0.06782 0.06381 -0.0581 0.0063 0.7433 14.750 1.3582 0.07221 0.06837 -0.0578 0.0064 0.7457 15.000 1.3482 0.07657 0.07289 -0.0581 0.0064 0.7482 15.250 1.3386 0.08113 0.07760 -0.0590 0.0064 0.7509 15.500 1.3222 0.08716 0.08383 -0.0607 0.0064 0.7533 15.750 1.3119 0.09247 0.08928 -0.0627 0.0064 0.7562