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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -1.0347 0.06047 0.05757 -0.0561 1.0000 0.0116 -16.000 -1.0547 0.05324 0.05015 -0.0612 1.0000 0.0116 -15.750 -1.0665 0.04796 0.04472 -0.0646 1.0000 0.0117 -15.500 -1.0731 0.04382 0.04044 -0.0670 1.0000 0.0117 -15.250 -1.0760 0.04043 0.03693 -0.0686 1.0000 0.0118 -15.000 -1.0756 0.03763 0.03401 -0.0696 1.0000 0.0118 -14.750 -1.0736 0.03514 0.03141 -0.0703 1.0000 0.0119 -14.500 -1.0695 0.03300 0.02916 -0.0706 1.0000 0.0119 -14.250 -1.0641 0.03113 0.02719 -0.0706 1.0000 0.0120 -14.000 -1.0587 0.02944 0.02540 -0.0701 1.0000 0.0121 -13.750 -1.0539 0.02802 0.02389 -0.0690 1.0000 0.0122 -13.500 -1.0463 0.02672 0.02250 -0.0681 1.0000 0.0122 -13.250 -1.0345 0.02552 0.02121 -0.0676 1.0000 0.0123 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0.4233 0.6934 1.250 0.6427 0.00781 0.00216 -0.1017 0.3973 0.6972 1.500 0.6712 0.00801 0.00228 -0.1019 0.3733 0.7016 1.750 0.6993 0.00826 0.00242 -0.1020 0.3446 0.7064 2.000 0.7266 0.00862 0.00259 -0.1020 0.3054 0.7108 2.250 0.7539 0.00897 0.00277 -0.1020 0.2699 0.7140 2.500 0.7814 0.00927 0.00295 -0.1021 0.2431 0.7167 2.750 0.8093 0.00950 0.00311 -0.1022 0.2247 0.7193 3.000 0.8371 0.00973 0.00327 -0.1022 0.2084 0.7221 3.250 0.8649 0.00997 0.00344 -0.1023 0.1936 0.7252 3.500 0.8926 0.01021 0.00362 -0.1023 0.1788 0.7283 3.750 0.9201 0.01047 0.00381 -0.1023 0.1645 0.7310 4.250 0.9749 0.01093 0.00421 -0.1023 0.1427 0.7376 4.500 1.0022 0.01117 0.00441 -0.1023 0.1341 0.7414 4.750 1.0294 0.01142 0.00462 -0.1023 0.1265 0.7447 5.000 1.0566 0.01165 0.00483 -0.1022 0.1203 0.7476 5.250 1.0838 0.01186 0.00506 -0.1022 0.1154 0.7510 5.500 1.1105 0.01211 0.00530 -0.1020 0.1098 0.7546 5.750 1.1375 0.01233 0.00553 -0.1019 0.1061 0.7584 6.000 1.1642 0.01258 0.00577 -0.1018 0.1012 0.7618 6.250 1.1901 0.01289 0.00605 -0.1016 0.0942 0.7651 6.500 1.2162 0.01316 0.00632 -0.1014 0.0887 0.7687 6.750 1.2417 0.01348 0.00662 -0.1011 0.0829 0.7729 7.000 1.2678 0.01373 0.00689 -0.1008 0.0804 0.7772 7.250 1.2934 0.01401 0.00718 -0.1006 0.0773 0.7809 7.500 1.3184 0.01434 0.00751 -0.1002 0.0737 0.7847 7.750 1.3435 0.01464 0.00783 -0.0998 0.0707 0.7888 8.000 1.3683 0.01495 0.00815 -0.0994 0.0675 0.7931 8.250 1.3924 0.01532 0.00852 -0.0989 0.0640 0.7971 8.500 1.4162 0.01567 0.00889 -0.0983 0.0611 0.8013 8.750 1.4403 0.01599 0.00925 -0.0978 0.0592 0.8057 9.000 1.4637 0.01635 0.00963 -0.0971 0.0565 0.8100 9.250 1.4859 0.01679 0.01007 -0.0963 0.0531 0.8138 9.500 1.5085 0.01717 0.01048 -0.0956 0.0506 0.8178 9.750 1.5299 0.01762 0.01095 -0.0947 0.0463 0.8224 10.000 1.5498 0.01816 0.01147 -0.0935 0.0408 0.8269 10.250 1.5671 0.01886 0.01213 -0.0920 0.0335 0.8310 10.500 1.5839 0.01953 0.01281 -0.0904 0.0292 0.8353 10.750 1.5992 0.02023 0.01352 -0.0885 0.0263 0.8399 11.000 1.6146 0.02084 0.01416 -0.0867 0.0245 0.8442 11.250 1.6255 0.02150 0.01487 -0.0840 0.0230 0.8485 11.500 1.6374 0.02226 0.01568 -0.0817 0.0217 0.8533 11.750 1.6512 0.02295 0.01643 -0.0798 0.0210 0.8581 12.000 1.6642 0.02371 0.01725 -0.0779 0.0203 0.8626 12.250 1.6764 0.02455 0.01816 -0.0760 0.0196 0.8679 12.500 1.6878 0.02548 0.01915 -0.0741 0.0190 0.8733 12.750 1.6983 0.02651 0.02025 -0.0722 0.0184 0.8784 13.000 1.7078 0.02764 0.02145 -0.0704 0.0177 0.8840 13.250 1.7188 0.02870 0.02259 -0.0688 0.0173 0.8898 13.500 1.7287 0.02986 0.02384 -0.0673 0.0169 0.8960 13.750 1.7376 0.03114 0.02520 -0.0658 0.0164 0.9033 14.000 1.7454 0.03253 0.02668 -0.0642 0.0160 0.9115 14.250 1.7521 0.03406 0.02829 -0.0628 0.0156 0.9219 14.500 1.7570 0.03566 0.03000 -0.0612 0.0152 0.9386 14.750 1.7587 0.03741 0.03185 -0.0594 0.0149 1.0000 15.000 1.7625 0.03949 0.03400 -0.0584 0.0145 1.0000 15.250 1.7678 0.04148 0.03608 -0.0576 0.0142 1.0000 15.500 1.7722 0.04360 0.03828 -0.0568 0.0140 1.0000 15.750 1.7751 0.04592 0.04068 -0.0562 0.0138 1.0000 16.000 1.7767 0.04844 0.04330 -0.0557 0.0135 1.0000 16.250 1.7771 0.05120 0.04614 -0.0554 0.0132 1.0000 16.500 1.7763 0.05416 0.04919 -0.0552 0.0130 1.0000 16.750 1.7740 0.05740 0.05252 -0.0552 0.0127 1.0000 17.000 1.7702 0.06095 0.05618 -0.0554 0.0125 1.0000 17.250 1.7650 0.06480 0.06013 -0.0559 0.0122 1.0000 17.500 1.7576 0.06904 0.06447 -0.0566 0.0120 1.0000 17.750 1.7483 0.07368 0.06921 -0.0576 0.0118 1.0000 18.000 1.7369 0.07878 0.07443 -0.0589 0.0116 1.0000 18.250 1.7255 0.08400 0.07977 -0.0604 0.0115 1.0000 18.500 1.7124 0.08957 0.08547 -0.0622 0.0114 1.0000 18.750 1.6974 0.09557 0.09161 -0.0644 0.0113 1.0000 19.000 1.6800 0.10209 0.09826 -0.0669 0.0112 1.0000 19.250 1.6598 0.10921 0.10552 -0.0699 0.0111 1.0000