XFOIL Version 6.96 Calculated polar for: FX 63-120 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3379 0.12513 0.12268 -0.0400 1.0000 0.0101 -11.250 -0.5855 0.03797 0.03502 -0.1095 0.9707 0.0130 -11.000 -0.5709 0.03185 0.02864 -0.1214 0.9562 0.0131 -10.750 -0.5438 0.02937 0.02603 -0.1276 0.9461 0.0134 -10.500 -0.5116 0.02729 0.02377 -0.1329 0.9402 0.0137 -10.250 -0.4803 0.02530 0.02158 -0.1373 0.9327 0.0142 -10.000 -0.4435 0.02270 0.01862 -0.1431 0.9278 0.0150 -9.750 -0.4042 0.02033 0.01584 -0.1484 0.9232 0.0158 -9.500 -0.3630 0.01970 0.01517 -0.1522 0.9185 0.0163 -9.250 -0.3209 0.01918 0.01458 -0.1559 0.9135 0.0168 -9.000 -0.2805 0.01844 0.01369 -0.1595 0.9071 0.0176 -8.750 -0.2430 0.01741 0.01243 -0.1625 0.8991 0.0185 -8.500 -0.2078 0.01643 0.01118 -0.1649 0.8907 0.0193 -8.250 -0.1757 0.01577 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0.5694 2.000 1.0197 0.00909 0.00292 -0.1808 0.5479 0.5834 2.250 1.0464 0.00925 0.00305 -0.1805 0.5342 0.5963 2.500 1.0729 0.00942 0.00319 -0.1802 0.5195 0.6086 2.750 1.0994 0.00960 0.00335 -0.1799 0.5046 0.6199 3.000 1.1255 0.00981 0.00352 -0.1795 0.4886 0.6305 3.250 1.1509 0.01006 0.00371 -0.1790 0.4706 0.6413 3.500 1.1764 0.01031 0.00393 -0.1786 0.4532 0.6519 3.750 1.2017 0.01058 0.00416 -0.1781 0.4369 0.6622 4.000 1.2269 0.01085 0.00439 -0.1776 0.4213 0.6726 4.250 1.2519 0.01113 0.00465 -0.1771 0.4056 0.6820 4.500 1.2766 0.01144 0.00491 -0.1765 0.3876 0.6918 4.750 1.3008 0.01177 0.00519 -0.1759 0.3666 0.7014 5.000 1.3245 0.01215 0.00549 -0.1752 0.3450 0.7110 5.250 1.3480 0.01253 0.00582 -0.1745 0.3239 0.7213 5.500 1.3707 0.01296 0.00618 -0.1736 0.2996 0.7314 5.750 1.3921 0.01349 0.00659 -0.1726 0.2720 0.7423 6.000 1.4130 0.01405 0.00706 -0.1715 0.2464 0.7556 6.250 1.4345 0.01454 0.00750 -0.1705 0.2267 0.7704 6.500 1.4556 0.01505 0.00796 -0.1694 0.2088 0.7868 6.750 1.4759 0.01557 0.00845 -0.1682 0.1911 0.8061 7.000 1.4955 0.01607 0.00896 -0.1668 0.1747 0.8295 7.250 1.5127 0.01654 0.00945 -0.1650 0.1590 0.8696 7.750 1.5425 0.01756 0.01042 -0.1604 0.1288 1.0000 8.000 1.5585 0.01824 0.01104 -0.1585 0.1138 1.0000 8.250 1.5731 0.01894 0.01168 -0.1564 0.1017 1.0000 8.750 1.6024 0.02031 0.01302 -0.1523 0.0860 1.0000 9.000 1.6157 0.02109 0.01380 -0.1502 0.0797 1.0000 9.250 1.6305 0.02178 0.01453 -0.1483 0.0751 1.0000 9.500 1.6433 0.02262 0.01537 -0.1462 0.0702 1.0000 9.750 1.6563 0.02346 0.01625 -0.1442 0.0663 1.0000 10.000 1.6695 0.02431 0.01714 -0.1423 0.0619 1.0000 10.250 1.6794 0.02542 0.01825 -0.1401 0.0566 1.0000 10.500 1.6914 0.02641 0.01928 -0.1383 0.0520 1.0000 10.750 1.7005 0.02765 0.02052 -0.1362 0.0475 1.0000 11.000 1.7113 0.02881 0.02172 -0.1345 0.0446 1.0000 11.250 1.7211 0.03008 0.02304 -0.1327 0.0421 1.0000 11.500 1.7292 0.03155 0.02454 -0.1309 0.0395 1.0000 11.750 1.7385 0.03296 0.02602 -0.1294 0.0378 1.0000 12.000 1.7471 0.03447 0.02760 -0.1278 0.0362 1.0000 12.250 1.7544 0.03615 0.02934 -0.1263 0.0345 1.0000 12.500 1.7603 0.03804 0.03128 -0.1249 0.0329 1.0000 12.750 1.7670 0.03989 0.03321 -0.1236 0.0316 1.0000 13.000 1.7740 0.04176 0.03518 -0.1224 0.0305 1.0000 13.250 1.7796 0.04383 0.03733 -0.1213 0.0292 1.0000 13.500 1.7837 0.04612 0.03970 -0.1203 0.0278 1.0000 13.750 1.7859 0.04871 0.04235 -0.1193 0.0265 1.0000 14.000 1.7917 0.05094 0.04469 -0.1185 0.0254 1.0000 14.250 1.7958 0.05345 0.04729 -0.1179 0.0239 1.0000 14.500 1.7979 0.05626 0.05018 -0.1173 0.0225 1.0000 14.750 1.7995 0.05922 0.05323 -0.1169 0.0212 1.0000 15.000 1.8016 0.06219 0.05630 -0.1166 0.0196 1.0000 15.250 1.8018 0.06549 0.05968 -0.1164 0.0182 1.0000 15.500 1.8011 0.06902 0.06330 -0.1164 0.0169 1.0000 15.750 1.7997 0.07275 0.06712 -0.1166 0.0156 1.0000 16.000 1.7966 0.07680 0.07125 -0.1170 0.0145 1.0000 16.250 1.7928 0.08108 0.07563 -0.1175 0.0135 1.0000 16.500 1.7890 0.08545 0.08012 -0.1183 0.0128 1.0000 16.750 1.7838 0.09015 0.08492 -0.1192 0.0120 1.0000 17.000 1.7771 0.09521 0.09009 -0.1205 0.0114 1.0000 17.250 1.7700 0.10040 0.09539 -0.1219 0.0109 1.0000 17.500 1.7639 0.10553 0.10066 -0.1235 0.0105 1.0000 17.750 1.7569 0.11088 0.10615 -0.1253 0.0100 1.0000 18.000 1.7500 0.11629 0.11169 -0.1274 0.0098 1.0000 18.250 1.7416 0.12204 0.11757 -0.1297 0.0095 1.0000 18.500 1.7328 0.12790 0.12355 -0.1322 0.0092 1.0000 18.750 1.7237 0.13389 0.12966 -0.1350 0.0089 1.0000 19.000 1.7140 0.14005 0.13594 -0.1381 0.0087 1.0000