XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0518 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0192 0.10416 0.09808 -0.0498 1.0000 0.0513 -18.750 -1.0457 0.09598 0.08963 -0.0543 1.0000 0.0519 -18.500 -1.0660 0.08915 0.08253 -0.0578 1.0000 0.0525 -18.250 -1.0703 0.08510 0.07838 -0.0596 1.0000 0.0530 -18.000 -1.0680 0.08213 0.07539 -0.0608 1.0000 0.0535 -17.750 -1.0667 0.07902 0.07222 -0.0621 1.0000 0.0541 -17.500 -1.0663 0.07581 0.06894 -0.0633 1.0000 0.0546 -17.250 -1.0662 0.07263 0.06567 -0.0645 1.0000 0.0552 -17.000 -1.0657 0.06957 0.06250 -0.0655 1.0000 0.0559 -16.750 -1.0649 0.06660 0.05941 -0.0664 1.0000 0.0566 -16.500 -1.0635 0.06377 0.05644 -0.0672 1.0000 0.0574 -16.250 -1.0617 0.06104 0.05354 -0.0678 1.0000 0.0582 -16.000 -1.0566 0.05880 0.05123 -0.0682 1.0000 0.0589 -15.750 -1.0489 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0.01452 0.00833 -0.0903 0.8243 0.6160 -1.500 0.1721 0.01471 0.00855 -0.0897 0.8185 0.6197 -1.250 0.2029 0.01477 0.00859 -0.0899 0.8135 0.6236 -1.000 0.2340 0.01471 0.00851 -0.0906 0.8043 0.6275 -0.750 0.2701 0.01445 0.00811 -0.0923 0.7909 0.6323 -0.500 0.2977 0.01437 0.00797 -0.0916 0.7719 0.6341 -0.250 0.3252 0.01433 0.00788 -0.0911 0.7530 0.6356 0.000 0.3535 0.01431 0.00784 -0.0909 0.7370 0.6370 0.250 0.3826 0.01429 0.00780 -0.0909 0.7229 0.6386 0.500 0.4124 0.01428 0.00774 -0.0910 0.7096 0.6403 0.750 0.4420 0.01427 0.00768 -0.0911 0.6929 0.6422 1.000 0.4715 0.01427 0.00762 -0.0913 0.6721 0.6443 1.250 0.5011 0.01430 0.00756 -0.0915 0.6463 0.6469 1.500 0.5311 0.01436 0.00749 -0.0918 0.6174 0.6500 1.750 0.5614 0.01445 0.00740 -0.0924 0.5790 0.6529 2.000 0.5867 0.01472 0.00739 -0.0918 0.5200 0.6546 2.250 0.6058 0.01531 0.00759 -0.0900 0.4390 0.6560 2.500 0.6245 0.01602 0.00792 -0.0883 0.3691 0.6576 2.750 0.6456 0.01662 0.00826 -0.0872 0.3163 0.6592 3.000 0.6680 0.01717 0.00858 -0.0863 0.2741 0.6607 3.500 0.7158 0.01809 0.00918 -0.0852 0.2119 0.6641 3.750 0.7404 0.01852 0.00948 -0.0848 0.1906 0.6660 4.000 0.7655 0.01892 0.00979 -0.0845 0.1744 0.6680 4.250 0.7913 0.01929 0.01008 -0.0843 0.1611 0.6701 4.500 0.8173 0.01967 0.01039 -0.0841 0.1502 0.6723 4.750 0.8432 0.02006 0.01071 -0.0840 0.1410 0.6744 5.000 0.8677 0.02044 0.01106 -0.0836 0.1329 0.6762 5.250 0.8903 0.02085 0.01146 -0.0826 0.1267 0.6778 5.500 0.9122 0.02129 0.01190 -0.0816 0.1211 0.6796 5.750 0.9341 0.02174 0.01235 -0.0806 0.1164 0.6815 6.000 0.9564 0.02218 0.01281 -0.0796 0.1118 0.6835 6.250 0.9771 0.02271 0.01329 -0.0786 0.1081 0.6855 6.500 0.9996 0.02314 0.01378 -0.0777 0.1044 0.6877 6.750 1.0209 0.02364 0.01427 -0.0768 0.1011 0.6900 7.000 1.0392 0.02423 0.01482 -0.0754 0.0983 0.6924 7.250 1.0595 0.02468 0.01533 -0.0742 0.0955 0.6949 7.500 1.0792 0.02521 0.01586 -0.0731 0.0927 0.6973 7.750 1.0967 0.02580 0.01648 -0.0715 0.0904 0.6992 8.000 1.1144 0.02645 0.01716 -0.0701 0.0883 0.7010 8.250 1.1334 0.02706 0.01786 -0.0688 0.0861 0.7030 8.500 1.1517 0.02772 0.01856 -0.0675 0.0839 0.7053 8.750 1.1691 0.02845 0.01930 -0.0662 0.0821 0.7079 9.000 1.1862 0.02925 0.02012 -0.0649 0.0803 0.7108 9.250 1.2047 0.02999 0.02094 -0.0638 0.0784 0.7139 9.500 1.2228 0.03080 0.02179 -0.0628 0.0767 0.7169 9.750 1.2403 0.03165 0.02266 -0.0619 0.0751 0.7198 10.000 1.2546 0.03260 0.02363 -0.0604 0.0738 0.7219 10.250 1.2699 0.03352 0.02464 -0.0590 0.0723 0.7241 10.500 1.2851 0.03446 0.02568 -0.0577 0.0707 0.7265 10.750 1.2997 0.03545 0.02675 -0.0564 0.0693 0.7292 11.000 1.3137 0.03652 0.02787 -0.0552 0.0680 0.7321 11.250 1.3269 0.03768 0.02906 -0.0540 0.0670 0.7352 11.500 1.3403 0.03892 0.03034 -0.0529 0.0659 0.7385 11.750 1.3547 0.04014 0.03167 -0.0520 0.0647 0.7420 12.000 1.3662 0.04141 0.03306 -0.0507 0.0635 0.7446 12.250 1.3770 0.04274 0.03449 -0.0494 0.0624 0.7473 12.500 1.3871 0.04414 0.03597 -0.0483 0.0614 0.7504 12.750 1.3967 0.04566 0.03753 -0.0472 0.0606 0.7538 13.000 1.4061 0.04728 0.03920 -0.0463 0.0597 0.7572 13.250 1.4156 0.04899 0.04107 -0.0455 0.0588 0.7608 13.500 1.4241 0.05080 0.04300 -0.0447 0.0578 0.7640 13.750 1.4305 0.05266 0.04499 -0.0437 0.0570 0.7664 14.000 1.4363 0.05463 0.04708 -0.0428 0.0563 0.7691 14.250 1.4416 0.05670 0.04924 -0.0421 0.0556 0.7722 14.500 1.4465 0.05887 0.05149 -0.0415 0.0550 0.7755 14.750 1.4509 0.06115 0.05384 -0.0412 0.0545 0.7790 15.000 1.4554 0.06356 0.05628 -0.0410 0.0539 0.7826 15.250 1.4557 0.06645 0.05939 -0.0407 0.0533 0.7852 15.500 1.4547 0.06950 0.06263 -0.0406 0.0526 0.7877 15.750 1.4533 0.07273 0.06603 -0.0408 0.0519 0.7907 16.000 1.4514 0.07614 0.06960 -0.0412 0.0513 0.7940 16.250 1.4490 0.07973 0.07333 -0.0419 0.0508 0.7975 16.500 1.4464 0.08351 0.07723 -0.0430 0.0503 0.8012 16.750 1.4428 0.08740 0.08124 -0.0441 0.0498 0.8040 17.000 1.4388 0.09138 0.08533 -0.0453 0.0494 0.8067 17.250 1.4349 0.09547 0.08953 -0.0467 0.0491 0.8096 17.500 1.4317 0.09954 0.09368 -0.0482 0.0487 0.8127 17.750 1.4245 0.10441 0.09868 -0.0504 0.0484 0.8158 18.000 1.4060 0.11162 0.10617 -0.0544 0.0480 0.8183