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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2174 0.08433 0.07916 -0.0574 1.0000 0.0470 -19.500 -1.2210 0.08052 0.07523 -0.0590 1.0000 0.0475 -19.250 -1.2164 0.07817 0.07288 -0.0595 1.0000 0.0481 -19.000 -1.2115 0.07566 0.07036 -0.0604 1.0000 0.0486 -18.750 -1.2080 0.07294 0.06760 -0.0615 1.0000 0.0491 -18.500 -1.2041 0.07028 0.06489 -0.0624 1.0000 0.0497 -18.250 -1.2011 0.06753 0.06208 -0.0634 1.0000 0.0502 -18.000 -1.1973 0.06492 0.05938 -0.0642 1.0000 0.0508 -17.750 -1.1941 0.06227 0.05664 -0.0650 1.0000 0.0514 -17.500 -1.1903 0.05973 0.05399 -0.0657 1.0000 0.0520 -17.250 -1.1861 0.05725 0.05138 -0.0664 1.0000 0.0525 -17.000 -1.1779 0.05551 0.04962 -0.0663 1.0000 0.0533 -16.750 -1.1686 0.05384 0.04796 -0.0664 1.0000 0.0540 -16.500 -1.1601 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-0.1019 0.3560 0.6561 2.750 0.7052 0.01272 0.00599 -0.1011 0.2985 0.6580 3.000 0.7292 0.01325 0.00628 -0.1004 0.2527 0.6598 3.250 0.7539 0.01371 0.00655 -0.0998 0.2152 0.6614 3.500 0.7790 0.01415 0.00682 -0.0994 0.1876 0.6629 3.750 0.8051 0.01451 0.00708 -0.0990 0.1688 0.6645 4.000 0.8312 0.01485 0.00734 -0.0987 0.1535 0.6662 4.250 0.8573 0.01520 0.00760 -0.0984 0.1415 0.6679 4.500 0.8834 0.01554 0.00787 -0.0981 0.1316 0.6697 4.750 0.9100 0.01584 0.00813 -0.0978 0.1243 0.6714 5.000 0.9353 0.01623 0.00845 -0.0974 0.1179 0.6730 5.250 0.9618 0.01653 0.00873 -0.0971 0.1128 0.6745 5.500 0.9860 0.01696 0.00910 -0.0965 0.1080 0.6761 5.750 1.0118 0.01718 0.00936 -0.0961 0.1046 0.6782 6.000 1.0359 0.01752 0.00970 -0.0954 0.1012 0.6800 6.250 1.0578 0.01801 0.01017 -0.0943 0.0978 0.6818 6.500 1.0825 0.01829 0.01049 -0.0936 0.0951 0.6838 6.750 1.1059 0.01864 0.01085 -0.0928 0.0924 0.6860 7.000 1.1266 0.01916 0.01134 -0.0915 0.0898 0.6883 7.250 1.1490 0.01955 0.01177 -0.0905 0.0877 0.6905 7.500 1.1717 0.01991 0.01214 -0.0896 0.0855 0.6927 7.750 1.1929 0.02032 0.01254 -0.0885 0.0833 0.6949 8.000 1.2075 0.02096 0.01315 -0.0862 0.0812 0.6967 8.250 1.2255 0.02133 0.01358 -0.0845 0.0796 0.6989 8.500 1.2446 0.02176 0.01406 -0.0830 0.0779 0.7015 8.750 1.2635 0.02227 0.01461 -0.0815 0.0762 0.7038 9.000 1.2801 0.02295 0.01528 -0.0799 0.0745 0.7061 9.250 1.2955 0.02375 0.01611 -0.0780 0.0729 0.7086 9.500 1.3150 0.02427 0.01670 -0.0768 0.0714 0.7112 9.750 1.3335 0.02487 0.01734 -0.0755 0.0698 0.7139 10.000 1.3511 0.02555 0.01802 -0.0742 0.0684 0.7167 10.250 1.3655 0.02648 0.01893 -0.0725 0.0671 0.7191 10.500 1.3804 0.02738 0.01989 -0.0710 0.0659 0.7219 10.750 1.3973 0.02807 0.02068 -0.0696 0.0647 0.7251 11.000 1.4131 0.02886 0.02154 -0.0682 0.0635 0.7280 11.250 1.4282 0.02972 0.02244 -0.0668 0.0624 0.7311 11.500 1.4425 0.03066 0.02342 -0.0653 0.0614 0.7342 11.750 1.4534 0.03193 0.02467 -0.0637 0.0603 0.7374 12.000 1.4670 0.03302 0.02583 -0.0624 0.0594 0.7405 12.250 1.4815 0.03401 0.02691 -0.0612 0.0584 0.7435 12.500 1.4947 0.03506 0.02806 -0.0599 0.0574 0.7467 12.750 1.5070 0.03622 0.02928 -0.0586 0.0565 0.7498 13.000 1.5185 0.03746 0.03057 -0.0574 0.0557 0.7532 13.250 1.5286 0.03886 0.03201 -0.0561 0.0550 0.7567 13.500 1.5357 0.04059 0.03374 -0.0546 0.0542 0.7603 13.750 1.5454 0.04214 0.03537 -0.0535 0.0536 0.7636 14.000 1.5547 0.04365 0.03702 -0.0524 0.0530 0.7672 14.250 1.5630 0.04528 0.03876 -0.0513 0.0523 0.7706 14.500 1.5707 0.04700 0.04057 -0.0503 0.0517 0.7742 14.750 1.5778 0.04883 0.04247 -0.0494 0.0510 0.7780 15.000 1.5848 0.05073 0.04444 -0.0487 0.0505 0.7816 15.250 1.5911 0.05274 0.04650 -0.0480 0.0499 0.7850 15.500 1.5956 0.05489 0.04871 -0.0473 0.0494 0.7881 15.750 1.5988 0.05719 0.05105 -0.0464 0.0488 0.7912 16.000 1.6012 0.05968 0.05363 -0.0457 0.0483 0.7946 16.250 1.6038 0.06233 0.05642 -0.0456 0.0479 0.7983 16.500 1.6057 0.06515 0.05936 -0.0456 0.0474 0.8018 16.750 1.6067 0.06804 0.06238 -0.0455 0.0470 0.8048 17.000 1.6068 0.07108 0.06554 -0.0456 0.0466 0.8077 17.250 1.6065 0.07424 0.06882 -0.0458 0.0462 0.8108 17.500 1.6057 0.07756 0.07225 -0.0463 0.0457 0.8142 17.750 1.6047 0.08102 0.07579 -0.0470 0.0454 0.8176 18.000 1.6034 0.08459 0.07944 -0.0478 0.0450 0.8208 18.250 1.6013 0.08819 0.08313 -0.0487 0.0447 0.8236 18.500 1.5991 0.09182 0.08684 -0.0496 0.0443 0.8264 18.750 1.5970 0.09546 0.09054 -0.0505 0.0440 0.8296 19.000 1.5939 0.09917 0.09431 -0.0514 0.0436 0.8329 19.250 1.5872 0.10355 0.09880 -0.0529 0.0433 0.8360