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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3114 0.11579 0.11225 -0.0432 1.0000 0.0493 -10.000 -0.3274 0.11381 0.11036 -0.0437 1.0000 0.0497 -9.750 -0.3449 0.11223 0.10888 -0.0425 1.0000 0.0498 -9.500 -0.3384 0.10878 0.10546 -0.0386 1.0000 0.0506 -9.250 -0.3391 0.10759 0.10432 -0.0350 1.0000 0.0512 -9.000 -0.3232 0.10502 0.10174 -0.0359 0.9982 0.0528 -8.750 -0.3043 0.10112 0.09784 -0.0408 0.9949 0.0557 -8.500 -0.3042 0.09437 0.09112 -0.0582 0.9855 0.0595 -8.250 -0.2846 0.08939 0.08613 -0.0583 0.9839 0.0609 -8.000 -0.2627 0.08691 0.08364 -0.0585 0.9793 0.0624 -7.750 -0.2418 0.08352 0.08024 -0.0624 0.9749 0.0652 -7.500 -0.2323 0.07907 0.07580 -0.0689 0.9655 0.0688 -7.250 -0.2280 0.06555 0.06227 -0.0944 0.9502 0.0725 -7.000 -0.2033 0.06640 0.06313 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0.8473 0.4917 -2.000 0.5399 0.01213 0.00590 -0.1796 0.8406 0.5206 -1.750 0.5665 0.01231 0.00612 -0.1789 0.8327 0.5457 -1.500 0.5950 0.01243 0.00623 -0.1786 0.8254 0.5672 -1.250 0.6230 0.01254 0.00632 -0.1783 0.8182 0.5836 -1.000 0.6509 0.01258 0.00635 -0.1780 0.8104 0.5959 -0.750 0.6809 0.01261 0.00631 -0.1782 0.8038 0.6080 -0.500 0.7077 0.01267 0.00638 -0.1778 0.7954 0.6203 -0.250 0.7380 0.01267 0.00634 -0.1780 0.7893 0.6316 0.000 0.7639 0.01272 0.00642 -0.1775 0.7802 0.6434 0.250 0.7943 0.01272 0.00637 -0.1777 0.7737 0.6570 0.500 0.8204 0.01280 0.00649 -0.1772 0.7647 0.6718 0.750 0.8495 0.01280 0.00647 -0.1771 0.7577 0.6865 1.000 0.8748 0.01287 0.00660 -0.1764 0.7484 0.7015 1.250 0.9036 0.01288 0.00659 -0.1763 0.7412 0.7176 1.500 0.9286 0.01295 0.00672 -0.1755 0.7313 0.7337 1.750 0.9566 0.01298 0.00673 -0.1752 0.7234 0.7502 2.000 0.9816 0.01301 0.00681 -0.1743 0.7128 0.7661 2.250 1.0072 0.01302 0.00685 -0.1735 0.7017 0.7816 2.500 1.0336 0.01300 0.00680 -0.1728 0.6910 0.7971 2.750 1.0580 0.01301 0.00685 -0.1719 0.6790 0.8128 3.000 1.0823 0.01304 0.00694 -0.1709 0.6677 0.8290 3.250 1.1070 0.01307 0.00698 -0.1700 0.6571 0.8465 3.500 1.1293 0.01307 0.00701 -0.1685 0.6456 0.8656 3.750 1.1496 0.01308 0.00710 -0.1667 0.6334 0.8895 4.000 1.1673 0.01300 0.00708 -0.1643 0.6218 0.9298 4.250 1.1953 0.01307 0.00712 -0.1643 0.6092 1.0000 4.500 1.2256 0.01327 0.00726 -0.1649 0.5957 1.0000 4.750 1.2536 0.01348 0.00745 -0.1650 0.5801 1.0000 5.000 1.2803 0.01370 0.00762 -0.1648 0.5630 1.0000 5.250 1.3056 0.01394 0.00783 -0.1644 0.5444 1.0000 5.500 1.3303 0.01421 0.00808 -0.1638 0.5253 1.0000 5.750 1.3546 0.01452 0.00835 -0.1631 0.5070 1.0000 6.000 1.3786 0.01488 0.00866 -0.1624 0.4896 1.0000 6.250 1.4020 0.01527 0.00902 -0.1616 0.4720 1.0000 6.500 1.4240 0.01573 0.00940 -0.1606 0.4526 1.0000 6.750 1.4448 0.01619 0.00983 -0.1593 0.4303 1.0000 7.000 1.4644 0.01673 0.01029 -0.1579 0.4074 1.0000 7.250 1.4833 0.01729 0.01081 -0.1564 0.3837 1.0000 7.500 1.5011 0.01789 0.01136 -0.1548 0.3596 1.0000 7.750 1.5178 0.01855 0.01196 -0.1530 0.3341 1.0000 8.000 1.5322 0.01932 0.01264 -0.1508 0.3079 1.0000 8.250 1.5449 0.02017 0.01341 -0.1485 0.2813 1.0000 8.500 1.5547 0.02111 0.01425 -0.1456 0.2560 1.0000 8.750 1.5609 0.02221 0.01523 -0.1424 0.2324 1.0000 9.000 1.5677 0.02336 0.01630 -0.1393 0.2083 1.0000 9.250 1.5719 0.02472 0.01755 -0.1360 0.1857 1.0000 9.500 1.5764 0.02616 0.01892 -0.1330 0.1632 1.0000 9.750 1.5786 0.02783 0.02048 -0.1299 0.1449 1.0000 10.000 1.5808 0.02961 0.02219 -0.1271 0.1299 1.0000 10.250 1.5833 0.03147 0.02402 -0.1245 0.1175 1.0000 10.500 1.5872 0.03334 0.02590 -0.1223 0.1072 1.0000 10.750 1.5893 0.03545 0.02803 -0.1200 0.0991 1.0000 11.000 1.5899 0.03779 0.03035 -0.1179 0.0924 1.0000 11.250 1.5939 0.03994 0.03259 -0.1162 0.0863 1.0000 11.500 1.5965 0.04228 0.03495 -0.1146 0.0813 1.0000 11.750 1.5985 0.04481 0.03751 -0.1130 0.0770 1.0000 12.000 1.6043 0.04696 0.03979 -0.1118 0.0729 1.0000 12.250 1.6071 0.04947 0.04232 -0.1106 0.0694 1.0000 12.500 1.6109 0.05207 0.04497 -0.1093 0.0661 1.0000 12.750 1.6163 0.05440 0.04746 -0.1084 0.0630 1.0000 13.000 1.6204 0.05692 0.05006 -0.1077 0.0602 1.0000 13.250 1.6244 0.05968 0.05275 -0.1066 0.0572 1.0000 13.500 1.6282 0.06236 0.05565 -0.1061 0.0550 1.0000 13.750 1.6315 0.06516 0.05859 -0.1056 0.0525 1.0000 14.000 1.6341 0.06806 0.06156 -0.1053 0.0503 1.0000 14.250 1.6396 0.07087 0.06433 -0.1045 0.0477 1.0000 14.500 1.6398 0.07423 0.06795 -0.1045 0.0460 1.0000 14.750 1.6409 0.07757 0.07145 -0.1045 0.0441 1.0000 15.000 1.6424 0.08085 0.07482 -0.1046 0.0424 1.0000 15.250 1.6468 0.08381 0.07774 -0.1044 0.0405 1.0000 15.500 1.6459 0.08766 0.08180 -0.1045 0.0390 1.0000 15.750 1.6431 0.09181 0.08617 -0.1052 0.0376 1.0000 16.000 1.6412 0.09583 0.09036 -0.1060 0.0363 1.0000 16.250 1.6411 0.09960 0.09423 -0.1068 0.0351 1.0000 16.500 1.6450 0.10270 0.09734 -0.1072 0.0339 1.0000 16.750 1.6441 0.10683 0.10163 -0.1077 0.0329 1.0000 17.000 1.6344 0.11238 0.10746 -0.1099 0.0322 1.0000 17.250 1.6260 0.11790 0.11323 -0.1121 0.0316 1.0000