XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0410 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6400 0.09360 0.08828 -0.0155 1.0000 0.1635 -9.000 -0.6184 0.09145 0.08610 -0.0124 1.0000 0.1683 -8.750 -0.6940 0.08276 0.07754 -0.0268 1.0000 0.1766 -8.500 -0.6375 0.08165 0.07644 -0.0177 1.0000 0.1822 -8.250 -0.7510 0.05202 0.04500 -0.0406 1.0000 0.0854 -8.000 -0.7382 0.04706 0.03989 -0.0406 1.0000 0.0833 -7.750 -0.7240 0.04254 0.03501 -0.0406 1.0000 0.0810 -7.500 -0.7066 0.03840 0.03039 -0.0407 1.0000 0.0797 -7.250 -0.6860 0.03505 0.02657 -0.0406 1.0000 0.0801 -7.000 -0.6631 0.03263 0.02371 -0.0404 1.0000 0.0832 -6.750 -0.6383 0.03066 0.02117 -0.0402 1.0000 0.0863 -6.500 -0.6158 0.02787 0.01836 -0.0398 1.0000 0.0898 -6.250 -0.5916 0.02647 0.01686 -0.0393 1.0000 0.0959 -6.000 -0.5666 0.02490 0.01501 -0.0388 1.0000 0.1017 -5.750 -0.5433 0.02349 0.01370 -0.0381 1.0000 0.1092 -5.500 -0.5186 0.02230 0.01236 -0.0374 1.0000 0.1166 -5.250 -0.4953 0.02114 0.01135 -0.0366 1.0000 0.1259 -5.000 -0.4716 0.02001 0.01030 -0.0358 1.0000 0.1351 -4.750 -0.4476 0.01906 0.00943 -0.0351 1.0000 0.1484 -4.500 -0.4233 0.01806 0.00863 -0.0346 1.0000 0.1658 -4.250 -0.3976 0.01694 0.00786 -0.0347 1.0000 0.1999 -4.000 -0.3756 0.01453 0.00797 -0.0341 1.0000 0.5530 -3.750 -0.3577 0.01577 0.00918 -0.0300 1.0000 0.6733 -3.500 -0.3440 0.01675 0.01011 -0.0251 1.0000 0.7060 -3.250 -0.3345 0.01761 0.01097 -0.0193 1.0000 0.7269 -3.000 -0.3231 0.01824 0.01156 -0.0143 1.0000 0.7460 -2.750 -0.3115 0.01872 0.01199 -0.0096 1.0000 0.7642 -2.500 -0.2992 0.01906 0.01229 -0.0052 1.0000 0.7820 -2.250 -0.2853 0.01931 0.01249 -0.0015 1.0000 0.8018 -2.000 -0.2806 0.01947 0.01266 0.0048 1.0000 0.8200 -1.750 -0.2747 0.01950 0.01269 0.0106 1.0000 0.8412 -1.500 -0.2655 0.01938 0.01255 0.0152 1.0000 0.8628 -1.250 -0.2564 0.01905 0.01219 0.0197 1.0000 0.8806 -1.000 -0.2426 0.01867 0.01179 0.0227 1.0000 0.8961 -0.750 -0.2256 0.01830 0.01138 0.0246 1.0000 0.9091 -0.500 -0.2054 0.01801 0.01105 0.0254 1.0000 0.9198 -0.250 -0.1854 0.01762 0.01065 0.0265 1.0000 0.9289 0.000 -0.1624 0.01737 0.01038 0.0266 1.0000 0.9362 0.250 -0.1375 0.01719 0.01019 0.0261 1.0000 0.9413 0.500 -0.1117 0.01712 0.01011 0.0253 1.0000 0.9455 0.750 -0.0863 0.01700 0.01002 0.0246 1.0000 0.9504 1.000 -0.0602 0.01697 0.01000 0.0238 1.0000 0.9554 1.250 -0.0330 0.01703 0.01010 0.0225 1.0000 0.9597 1.500 -0.0057 0.01708 0.01021 0.0213 1.0000 0.9640 1.750 0.0219 0.01723 0.01042 0.0199 1.0000 0.9684 2.000 0.0684 0.01754 0.01083 0.0150 0.9915 0.9707 2.250 0.1454 0.01771 0.01114 0.0055 0.9656 0.9702 2.500 0.2174 0.01739 0.01098 -0.0022 0.9393 0.9699 2.750 0.2936 0.01647 0.01028 -0.0092 0.9084 0.9687 3.000 0.3499 0.01547 0.00948 -0.0123 0.8752 0.9691 3.250 0.3921 0.01456 0.00870 -0.0127 0.8248 0.9706 3.500 0.4264 0.01392 0.00788 -0.0111 0.7022 0.9725 3.750 0.4387 0.01606 0.00770 -0.0071 0.2815 0.9754 4.000 0.4616 0.01762 0.00850 -0.0069 0.1931 0.9792 4.250 0.4883 0.01867 0.00932 -0.0071 0.1647 0.9829 4.500 0.5195 0.01968 0.01023 -0.0081 0.1460 0.9861 4.750 0.5522 0.02082 0.01128 -0.0094 0.1327 0.9896 5.000 0.5849 0.02220 0.01253 -0.0107 0.1219 0.9938 5.250 0.6197 0.02326 0.01374 -0.0123 0.1116 0.9988 5.500 0.6423 0.02473 0.01527 -0.0117 0.1052 1.0000 5.750 0.6655 0.02582 0.01651 -0.0112 0.0979 1.0000 6.000 0.6914 0.02799 0.01874 -0.0115 0.0927 1.0000 6.250 0.7176 0.02950 0.02070 -0.0114 0.0872 1.0000 6.500 0.7450 0.03149 0.02290 -0.0118 0.0834 1.0000 6.750 0.7717 0.03420 0.02581 -0.0124 0.0812 1.0000 7.000 0.7946 0.03836 0.03032 -0.0128 0.0797 1.0000 7.250 0.8157 0.04115 0.03377 -0.0124 0.0783 1.0000 7.500 0.8349 0.04523 0.03832 -0.0124 0.0784 1.0000 7.750 0.8565 0.04984 0.04317 -0.0130 0.0803 1.0000 8.250 0.7920 0.08027 0.07623 -0.0210 0.1622 1.0000 8.500 0.7968 0.08453 0.08054 -0.0228 0.1566 1.0000 8.750 0.8536 0.08922 0.08495 -0.0192 0.1527 1.0000 9.000 0.7653 0.09829 0.09432 -0.0359 0.1476 1.0000 9.250 0.7671 0.10318 0.09920 -0.0393 0.1423 1.0000 9.500 0.8358 0.10375 0.09975 -0.0260 0.1376 1.0000 9.750 0.7713 0.11378 0.10976 -0.0445 0.1358 1.0000 10.000 0.7599 0.11949 0.11543 -0.0510 0.1297 1.0000 10.250 0.7731 0.12311 0.11908 -0.0511 0.1256 1.0000 10.500 0.6071 0.11995 0.11603 -0.0304 0.1364 1.0000 10.750 0.5864 0.12427 0.12033 -0.0347 0.1309 1.0000