XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0412 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1477 0.12904 0.12627 -0.0043 1.0000 0.0136 -19.500 -1.2094 0.11306 0.11008 -0.0133 1.0000 0.0135 -19.250 -1.2648 0.09872 0.09552 -0.0212 1.0000 0.0134 -19.000 -1.3053 0.08743 0.08403 -0.0274 1.0000 0.0134 -18.750 -1.3333 0.07863 0.07505 -0.0323 1.0000 0.0134 -18.500 -1.3533 0.07152 0.06780 -0.0362 1.0000 0.0135 -18.250 -1.3673 0.06564 0.06177 -0.0393 1.0000 0.0135 -18.000 -1.3771 0.06070 0.05671 -0.0416 1.0000 0.0136 -17.750 -1.3839 0.05639 0.05228 -0.0435 1.0000 0.0136 -17.500 -1.3878 0.05268 0.04846 -0.0449 1.0000 0.0137 -17.250 -1.3901 0.04935 0.04503 -0.0460 1.0000 0.0138 -17.000 -1.3903 0.04641 0.04199 -0.0467 1.0000 0.0139 -16.750 -1.3893 0.04378 0.03926 -0.0472 1.0000 0.0140 -16.500 -1.3868 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0.00592 0.00153 -0.0761 0.8405 0.4626 -1.750 0.0644 0.00567 0.00145 -0.0772 0.8159 0.5396 -1.500 0.0942 0.00568 0.00144 -0.0775 0.7880 0.5681 -1.250 0.1240 0.00572 0.00146 -0.0778 0.7650 0.5945 -1.000 0.1535 0.00580 0.00148 -0.0780 0.7407 0.6109 -0.750 0.1822 0.00598 0.00152 -0.0780 0.6983 0.6231 -0.500 0.2107 0.00619 0.00155 -0.0781 0.6459 0.6291 -0.250 0.2373 0.00675 0.00167 -0.0779 0.5294 0.6366 0.000 0.2638 0.00744 0.00184 -0.0778 0.3981 0.6434 0.250 0.2921 0.00776 0.00196 -0.0779 0.3385 0.6482 0.500 0.3204 0.00808 0.00208 -0.0780 0.2820 0.6524 0.750 0.3487 0.00841 0.00219 -0.0782 0.2287 0.6561 1.000 0.3773 0.00869 0.00229 -0.0783 0.1903 0.6588 1.250 0.4058 0.00893 0.00240 -0.0784 0.1587 0.6610 1.500 0.4347 0.00910 0.00250 -0.0786 0.1406 0.6627 1.750 0.4635 0.00928 0.00261 -0.0787 0.1233 0.6642 2.000 0.4922 0.00946 0.00273 -0.0788 0.1089 0.6658 2.250 0.5210 0.00963 0.00285 -0.0789 0.0979 0.6674 2.500 0.5497 0.00982 0.00297 -0.0790 0.0862 0.6690 2.750 0.5782 0.01001 0.00310 -0.0791 0.0768 0.6707 3.000 0.6069 0.01018 0.00324 -0.0792 0.0704 0.6724 3.250 0.6354 0.01037 0.00339 -0.0793 0.0646 0.6740 3.500 0.6640 0.01054 0.00354 -0.0793 0.0609 0.6755 3.750 0.6923 0.01074 0.00370 -0.0794 0.0568 0.6770 4.000 0.7208 0.01090 0.00387 -0.0794 0.0541 0.6790 4.250 0.7490 0.01109 0.00404 -0.0794 0.0512 0.6808 4.500 0.7771 0.01130 0.00424 -0.0794 0.0485 0.6825 4.750 0.8053 0.01148 0.00443 -0.0794 0.0465 0.6842 5.000 0.8333 0.01169 0.00463 -0.0793 0.0441 0.6859 5.250 0.8611 0.01192 0.00485 -0.0793 0.0418 0.6876 5.500 0.8890 0.01212 0.00505 -0.0792 0.0400 0.6893 5.750 0.9166 0.01235 0.00527 -0.0791 0.0379 0.6909 6.000 0.9441 0.01260 0.00551 -0.0790 0.0360 0.6924 6.250 0.9716 0.01283 0.00575 -0.0789 0.0345 0.6938 6.500 0.9989 0.01308 0.00600 -0.0787 0.0326 0.6953 6.750 1.0259 0.01336 0.00627 -0.0786 0.0309 0.6971 7.000 1.0530 0.01361 0.00655 -0.0784 0.0294 0.6991 7.250 1.0797 0.01390 0.00685 -0.0781 0.0277 0.7011 7.500 1.1062 0.01422 0.00717 -0.0779 0.0264 0.7032 7.750 1.1328 0.01451 0.00749 -0.0776 0.0254 0.7054 8.000 1.1591 0.01483 0.00783 -0.0773 0.0243 0.7075 8.250 1.1850 0.01519 0.00819 -0.0769 0.0233 0.7094 8.500 1.2107 0.01557 0.00858 -0.0765 0.0225 0.7111 8.750 1.2365 0.01591 0.00895 -0.0762 0.0219 0.7125 9.000 1.2620 0.01626 0.00934 -0.0757 0.0212 0.7145 9.250 1.2872 0.01665 0.00976 -0.0753 0.0205 0.7165 9.500 1.3120 0.01706 0.01021 -0.0748 0.0199 0.7188 9.750 1.3363 0.01753 0.01071 -0.0742 0.0193 0.7211 10.000 1.3605 0.01799 0.01120 -0.0736 0.0189 0.7233 10.250 1.3848 0.01841 0.01168 -0.0730 0.0185 0.7255 10.500 1.4086 0.01885 0.01217 -0.0723 0.0181 0.7276 10.750 1.4321 0.01932 0.01268 -0.0716 0.0177 0.7295 11.250 1.4778 0.02032 0.01377 -0.0700 0.0168 0.7335 11.500 1.4997 0.02088 0.01438 -0.0691 0.0165 0.7359 11.750 1.5208 0.02150 0.01505 -0.0681 0.0161 0.7383 12.000 1.5407 0.02220 0.01581 -0.0669 0.0158 0.7407 12.250 1.5613 0.02279 0.01647 -0.0658 0.0156 0.7432 12.500 1.5812 0.02340 0.01715 -0.0646 0.0155 0.7457 12.750 1.6002 0.02405 0.01787 -0.0633 0.0153 0.7479 13.000 1.6183 0.02472 0.01862 -0.0619 0.0151 0.7503 13.250 1.6354 0.02543 0.01941 -0.0604 0.0149 0.7529 13.500 1.6511 0.02617 0.02024 -0.0586 0.0147 0.7557 13.750 1.6648 0.02695 0.02109 -0.0566 0.0146 0.7587 14.000 1.6754 0.02775 0.02198 -0.0540 0.0144 0.7618 14.250 1.6836 0.02863 0.02293 -0.0512 0.0143 0.7648 14.500 1.6924 0.02961 0.02400 -0.0486 0.0141 0.7677 14.750 1.7004 0.03069 0.02518 -0.0462 0.0140 0.7710 15.000 1.7077 0.03189 0.02647 -0.0439 0.0138 0.7743 15.250 1.7136 0.03323 0.02790 -0.0416 0.0137 0.7776 15.500 1.7184 0.03472 0.02949 -0.0395 0.0136 0.7806 15.750 1.7216 0.03641 0.03128 -0.0375 0.0135 0.7836 16.000 1.7232 0.03834 0.03332 -0.0357 0.0134 0.7869 16.250 1.7223 0.04058 0.03569 -0.0341 0.0132 0.7906 16.500 1.7193 0.04320 0.03842 -0.0328 0.0131 0.7943 16.750 1.7136 0.04626 0.04161 -0.0319 0.0130 0.7979 17.000 1.7053 0.04982 0.04532 -0.0315 0.0129 0.8014 17.250 1.6965 0.05373 0.04938 -0.0316 0.0129 0.8052 17.500 1.6861 0.05811 0.05391 -0.0324 0.0129 0.8090 17.750 1.6727 0.06328 0.05923 -0.0340 0.0128 0.8123 18.000 1.6529 0.06997 0.06610 -0.0369 0.0128 0.8150 18.250 1.6249 0.07877 0.07510 -0.0417 0.0128 0.8172 18.500 1.5772 0.09229 0.08888 -0.0498 0.0129 0.8182 18.750 1.4947 0.11308 0.11000 -0.0620 0.0129 0.8169 19.000 1.4090 0.13471 0.13192 -0.0748 0.0131 0.8151