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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.3213 0.07392 0.06939 -0.0555 1.0000 0.0396 -19.500 -1.3197 0.07095 0.06636 -0.0566 1.0000 0.0401 -19.250 -1.3172 0.06812 0.06347 -0.0575 1.0000 0.0405 -19.000 -1.3142 0.06538 0.06067 -0.0584 1.0000 0.0410 -18.750 -1.3087 0.06297 0.05820 -0.0591 1.0000 0.0414 -18.500 -1.3031 0.06060 0.05575 -0.0598 1.0000 0.0418 -18.250 -1.2943 0.05863 0.05372 -0.0604 1.0000 0.0422 -18.000 -1.2953 0.05565 0.05070 -0.0610 1.0000 0.0429 -17.750 -1.2905 0.05334 0.04836 -0.0615 1.0000 0.0436 -17.500 -1.2839 0.05121 0.04620 -0.0619 1.0000 0.0441 -17.250 -1.2748 0.04941 0.04437 -0.0622 1.0000 0.0447 -17.000 -1.2649 0.04772 0.04264 -0.0625 1.0000 0.0453 -16.750 -1.2550 0.04601 0.04088 -0.0627 1.0000 0.0459 -16.500 -1.2431 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0.2023 0.6247 2.750 0.7309 0.01108 0.00448 -0.1083 0.1808 0.6262 3.000 0.7587 0.01136 0.00466 -0.1083 0.1636 0.6279 3.250 0.7865 0.01164 0.00484 -0.1081 0.1483 0.6294 3.500 0.8143 0.01190 0.00503 -0.1081 0.1353 0.6307 3.750 0.8420 0.01217 0.00522 -0.1079 0.1247 0.6318 4.000 0.8697 0.01242 0.00541 -0.1078 0.1166 0.6326 4.250 0.8972 0.01264 0.00559 -0.1077 0.1095 0.6348 4.500 0.9250 0.01284 0.00578 -0.1076 0.1045 0.6369 4.750 0.9520 0.01311 0.00601 -0.1073 0.0995 0.6387 5.000 0.9795 0.01331 0.00622 -0.1071 0.0960 0.6404 5.250 1.0067 0.01355 0.00644 -0.1069 0.0923 0.6421 5.500 1.0332 0.01383 0.00670 -0.1065 0.0887 0.6437 5.750 1.0602 0.01404 0.00692 -0.1063 0.0863 0.6455 6.000 1.0865 0.01431 0.00716 -0.1059 0.0836 0.6472 6.250 1.1120 0.01464 0.00746 -0.1054 0.0808 0.6489 6.500 1.1386 0.01486 0.00770 -0.1050 0.0789 0.6506 6.750 1.1642 0.01515 0.00797 -0.1045 0.0768 0.6521 7.000 1.1887 0.01551 0.00830 -0.1038 0.0745 0.6535 7.250 1.2134 0.01581 0.00862 -0.1031 0.0728 0.6560 7.500 1.2388 0.01605 0.00890 -0.1026 0.0713 0.6589 7.750 1.2631 0.01634 0.00921 -0.1019 0.0696 0.6612 8.000 1.2862 0.01671 0.00957 -0.1010 0.0679 0.6634 8.250 1.3082 0.01712 0.00999 -0.0998 0.0661 0.6656 8.500 1.3318 0.01739 0.01029 -0.0990 0.0648 0.6678 8.750 1.3542 0.01771 0.01063 -0.0979 0.0634 0.6700 9.000 1.3751 0.01808 0.01100 -0.0966 0.0620 0.6721 9.250 1.3932 0.01856 0.01147 -0.0949 0.0605 0.6739 9.500 1.4089 0.01897 0.01191 -0.0926 0.0594 0.6754 9.750 1.4284 0.01932 0.01231 -0.0911 0.0584 0.6791 10.000 1.4479 0.01974 0.01277 -0.0896 0.0572 0.6822 10.250 1.4665 0.02023 0.01327 -0.0881 0.0560 0.6851 10.500 1.4833 0.02083 0.01388 -0.0864 0.0547 0.6879 10.750 1.5002 0.02144 0.01452 -0.0847 0.0536 0.6907 11.000 1.5191 0.02193 0.01506 -0.0833 0.0527 0.6935 11.250 1.5370 0.02250 0.01565 -0.0819 0.0517 0.6960 11.500 1.5540 0.02313 0.01630 -0.0803 0.0508 0.6986 11.750 1.5699 0.02384 0.01705 -0.0787 0.0498 0.7031 12.000 1.5826 0.02476 0.01800 -0.0768 0.0488 0.7067 12.250 1.5977 0.02555 0.01885 -0.0752 0.0481 0.7101 12.500 1.6140 0.02628 0.01963 -0.0738 0.0475 0.7135 12.750 1.6291 0.02709 0.02049 -0.0724 0.0468 0.7167 13.000 1.6437 0.02796 0.02140 -0.0709 0.0461 0.7194 13.250 1.6573 0.02892 0.02240 -0.0695 0.0454 0.7233 13.500 1.6697 0.02999 0.02352 -0.0680 0.0447 0.7274 13.750 1.6792 0.03130 0.02487 -0.0663 0.0439 0.7312 14.000 1.6868 0.03277 0.02640 -0.0645 0.0432 0.7348 14.250 1.7001 0.03384 0.02754 -0.0633 0.0428 0.7384 14.500 1.7120 0.03504 0.02879 -0.0621 0.0424 0.7416 14.750 1.7232 0.03632 0.03015 -0.0609 0.0418 0.7458 15.000 1.7332 0.03771 0.03161 -0.0596 0.0414 0.7500 15.250 1.7419 0.03924 0.03321 -0.0584 0.0409 0.7539 15.500 1.7498 0.04088 0.03490 -0.0573 0.0404 0.7576 15.750 1.7562 0.04270 0.03677 -0.0562 0.0400 0.7610 16.000 1.7602 0.04481 0.03892 -0.0551 0.0395 0.7637 16.250 1.7611 0.04726 0.04147 -0.0541 0.0391 0.7677 16.500 1.7586 0.05016 0.04446 -0.0531 0.0386 0.7711 16.750 1.7647 0.05224 0.04663 -0.0525 0.0384 0.7747 17.000 1.7697 0.05451 0.04898 -0.0520 0.0381 0.7781 17.250 1.7726 0.05704 0.05159 -0.0516 0.0379 0.7813 17.500 1.7749 0.05970 0.05434 -0.0513 0.0375 0.7841 17.750 1.7758 0.06259 0.05733 -0.0512 0.0373 0.7877 18.000 1.7758 0.06564 0.06048 -0.0512 0.0370 0.7909 18.250 1.7741 0.06898 0.06392 -0.0514 0.0367 0.7940 18.500 1.7715 0.07250 0.06752 -0.0517 0.0364 0.7971 18.750 1.7671 0.07632 0.07144 -0.0523 0.0362 0.7999 19.000 1.7609 0.08051 0.07571 -0.0531 0.0359 0.8023 19.250 1.7534 0.08497 0.08028 -0.0542 0.0357 0.8051