XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.7713 0.06169 0.05854 -0.0582 1.0000 0.0160 -13.250 -0.7991 0.05345 0.05007 -0.0647 1.0000 0.0160 -13.000 -0.8194 0.04765 0.04406 -0.0682 1.0000 0.0160 -12.750 -0.8345 0.04328 0.03947 -0.0699 1.0000 0.0160 -12.500 -0.8465 0.03984 0.03583 -0.0701 1.0000 0.0160 -12.250 -0.8585 0.03728 0.03310 -0.0685 1.0000 0.0160 -12.000 -0.8637 0.03494 0.03057 -0.0673 1.0000 0.0161 -11.750 -0.8631 0.03292 0.02834 -0.0657 1.0000 0.0161 -11.500 -0.8588 0.03116 0.02640 -0.0640 1.0000 0.0162 -11.250 -0.8419 0.02928 0.02430 -0.0644 0.9982 0.0162 -11.000 -0.8160 0.02751 0.02229 -0.0662 0.9952 0.0163 -10.750 -0.7891 0.02591 0.02050 -0.0678 0.9924 0.0164 -10.500 -0.7632 0.02415 0.01858 -0.0692 0.9887 0.0166 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0.6863 0.6869 -0.750 0.4036 0.00769 0.00232 -0.0979 0.6705 0.6961 -0.500 0.4325 0.00776 0.00236 -0.0980 0.6575 0.7023 -0.250 0.4618 0.00784 0.00239 -0.0982 0.6456 0.7063 0.000 0.4912 0.00792 0.00240 -0.0985 0.6304 0.7102 0.250 0.5201 0.00804 0.00243 -0.0986 0.6100 0.7143 0.500 0.5483 0.00818 0.00249 -0.0986 0.5853 0.7187 0.750 0.5766 0.00835 0.00256 -0.0987 0.5611 0.7238 1.000 0.6053 0.00852 0.00262 -0.0988 0.5380 0.7286 1.250 0.6333 0.00871 0.00272 -0.0989 0.5131 0.7324 1.500 0.6612 0.00890 0.00283 -0.0989 0.4892 0.7361 1.750 0.6891 0.00913 0.00296 -0.0989 0.4632 0.7396 2.000 0.7167 0.00940 0.00309 -0.0989 0.4344 0.7428 2.250 0.7445 0.00967 0.00324 -0.0990 0.4071 0.7459 2.500 0.7716 0.00996 0.00341 -0.0990 0.3778 0.7488 2.750 0.7981 0.01031 0.00362 -0.0988 0.3423 0.7518 3.000 0.8242 0.01072 0.00386 -0.0986 0.3049 0.7550 3.250 0.8504 0.01113 0.00410 -0.0985 0.2717 0.7584 3.500 0.8771 0.01149 0.00434 -0.0984 0.2465 0.7622 3.750 0.9036 0.01182 0.00459 -0.0983 0.2260 0.7655 4.000 0.9300 0.01213 0.00484 -0.0981 0.2085 0.7687 4.250 0.9564 0.01245 0.00510 -0.0980 0.1927 0.7720 4.500 0.9829 0.01277 0.00537 -0.0979 0.1777 0.7755 4.750 1.0092 0.01310 0.00564 -0.0977 0.1642 0.7793 5.000 1.0352 0.01342 0.00592 -0.0975 0.1526 0.7825 5.250 1.0612 0.01371 0.00622 -0.0972 0.1438 0.7858 5.500 1.0868 0.01406 0.00653 -0.0969 0.1355 0.7893 5.750 1.1128 0.01436 0.00683 -0.0967 0.1286 0.7931 6.000 1.1381 0.01473 0.00718 -0.0964 0.1219 0.7971 6.250 1.1636 0.01500 0.00750 -0.0961 0.1174 0.8005 6.500 1.1885 0.01534 0.00785 -0.0956 0.1125 0.8043 6.750 1.2131 0.01572 0.00823 -0.0952 0.1075 0.8083 7.000 1.2382 0.01605 0.00858 -0.0949 0.1021 0.8123 7.250 1.2615 0.01647 0.00898 -0.0942 0.0958 0.8158 7.500 1.2855 0.01680 0.00936 -0.0937 0.0917 0.8198 7.750 1.3092 0.01718 0.00977 -0.0931 0.0877 0.8243 8.000 1.3322 0.01763 0.01020 -0.0924 0.0839 0.8288 8.250 1.3550 0.01800 0.01063 -0.0917 0.0810 0.8324 8.500 1.3774 0.01839 0.01108 -0.0909 0.0775 0.8365 8.750 1.3990 0.01885 0.01156 -0.0900 0.0743 0.8412 9.000 1.4200 0.01934 0.01207 -0.0891 0.0713 0.8458 9.250 1.4409 0.01975 0.01255 -0.0880 0.0688 0.8501 9.500 1.4608 0.02023 0.01308 -0.0869 0.0656 0.8548 9.750 1.4796 0.02080 0.01366 -0.0856 0.0624 0.8597 10.000 1.4975 0.02130 0.01423 -0.0842 0.0599 0.8639 10.250 1.5143 0.02182 0.01481 -0.0825 0.0570 0.8689 10.500 1.5272 0.02244 0.01547 -0.0803 0.0538 0.8744 10.750 1.5409 0.02309 0.01619 -0.0782 0.0508 0.8795 11.000 1.5548 0.02378 0.01694 -0.0763 0.0467 0.8856 11.250 1.5672 0.02462 0.01780 -0.0744 0.0423 0.8919 11.750 1.5880 0.02660 0.01986 -0.0703 0.0340 0.9059 12.250 1.6050 0.02891 0.02230 -0.0662 0.0295 0.9238 12.500 1.6115 0.03017 0.02364 -0.0641 0.0279 0.9380 13.000 1.6224 0.03306 0.02669 -0.0603 0.0257 1.0000 13.250 1.6309 0.03463 0.02835 -0.0592 0.0248 1.0000 13.500 1.6379 0.03637 0.03018 -0.0581 0.0240 1.0000 13.750 1.6432 0.03831 0.03220 -0.0570 0.0231 1.0000 14.000 1.6469 0.04047 0.03444 -0.0561 0.0225 1.0000 14.250 1.6484 0.04292 0.03698 -0.0552 0.0219 1.0000 14.500 1.6506 0.04535 0.03951 -0.0546 0.0214 1.0000 14.750 1.6536 0.04775 0.04203 -0.0541 0.0209 1.0000 15.000 1.6551 0.05040 0.04479 -0.0537 0.0205 1.0000 15.250 1.6549 0.05332 0.04782 -0.0535 0.0200 1.0000 15.500 1.6529 0.05652 0.05114 -0.0535 0.0196 1.0000 15.750 1.6496 0.06002 0.05476 -0.0537 0.0193 1.0000 16.000 1.6446 0.06388 0.05873 -0.0541 0.0189 1.0000 16.250 1.6375 0.06815 0.06312 -0.0549 0.0186 1.0000 16.500 1.6286 0.07282 0.06791 -0.0560 0.0183 1.0000 16.750 1.6171 0.07804 0.07325 -0.0574 0.0180 1.0000 17.000 1.6032 0.08381 0.07915 -0.0593 0.0178 1.0000 17.250 1.5913 0.08938 0.08486 -0.0612 0.0176 1.0000 17.500 1.5783 0.09526 0.09089 -0.0634 0.0174 1.0000 17.750 1.5637 0.10153 0.09730 -0.0659 0.0173 1.0000 18.000 1.5473 0.10824 0.10416 -0.0688 0.0172 1.0000 18.250 1.5292 0.11533 0.11141 -0.0720 0.0170 1.0000 18.500 1.5109 0.12266 0.11888 -0.0755 0.0169 1.0000 18.750 1.4925 0.13013 0.12649 -0.0793 0.0168 1.0000