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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.1059 0.12730 0.12472 -0.0058 1.0000 0.0172 -19.000 -1.1447 0.11529 0.11253 -0.0127 1.0000 0.0172 -18.750 -1.1776 0.10484 0.10192 -0.0186 1.0000 0.0172 -18.500 -1.2045 0.09572 0.09265 -0.0237 1.0000 0.0172 -18.250 -1.2275 0.08756 0.08433 -0.0284 1.0000 0.0172 -18.000 -1.2454 0.08041 0.07704 -0.0324 1.0000 0.0172 -17.750 -1.2602 0.07405 0.07053 -0.0359 1.0000 0.0173 -17.500 -1.2715 0.06847 0.06482 -0.0389 1.0000 0.0173 -17.250 -1.2798 0.06356 0.05978 -0.0413 1.0000 0.0174 -17.000 -1.2851 0.05932 0.05542 -0.0433 1.0000 0.0174 -16.750 -1.2908 0.05523 0.05121 -0.0449 1.0000 0.0175 -16.500 -1.3034 0.05058 0.04642 -0.0464 1.0000 0.0176 -16.250 -1.3115 0.04674 0.04245 -0.0473 1.0000 0.0178 -16.000 -1.3155 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0.1126 0.6999 3.000 0.6065 0.01016 0.00354 -0.0786 0.0975 0.7015 3.250 0.6347 0.01038 0.00371 -0.0786 0.0852 0.7032 3.500 0.6629 0.01062 0.00389 -0.0786 0.0767 0.7050 3.750 0.6913 0.01081 0.00406 -0.0787 0.0718 0.7068 4.000 0.7193 0.01107 0.00428 -0.0786 0.0660 0.7085 4.250 0.7477 0.01125 0.00446 -0.0787 0.0632 0.7103 4.500 0.7759 0.01147 0.00465 -0.0787 0.0598 0.7119 4.750 0.8037 0.01175 0.00490 -0.0786 0.0561 0.7134 5.000 0.8319 0.01189 0.00507 -0.0786 0.0541 0.7157 5.250 0.8596 0.01210 0.00527 -0.0786 0.0514 0.7175 5.500 0.8869 0.01240 0.00557 -0.0784 0.0484 0.7192 5.750 0.9147 0.01259 0.00578 -0.0783 0.0465 0.7210 6.000 0.9422 0.01284 0.00602 -0.0782 0.0443 0.7228 6.250 0.9689 0.01320 0.00637 -0.0779 0.0418 0.7247 6.500 0.9965 0.01340 0.00660 -0.0778 0.0400 0.7265 6.750 1.0236 0.01367 0.00685 -0.0777 0.0380 0.7283 7.000 1.0500 0.01406 0.00723 -0.0774 0.0359 0.7299 7.250 1.0772 0.01429 0.00748 -0.0772 0.0344 0.7315 7.500 1.1039 0.01456 0.00777 -0.0770 0.0328 0.7340 7.750 1.1292 0.01503 0.00824 -0.0765 0.0311 0.7362 8.000 1.1557 0.01531 0.00857 -0.0762 0.0301 0.7384 8.250 1.1817 0.01563 0.00892 -0.0759 0.0290 0.7406 8.500 1.2073 0.01601 0.00931 -0.0755 0.0279 0.7429 8.750 1.2311 0.01664 0.00996 -0.0748 0.0266 0.7450 9.000 1.2567 0.01699 0.01035 -0.0743 0.0260 0.7470 9.250 1.2819 0.01740 0.01079 -0.0739 0.0253 0.7486 9.500 1.3066 0.01780 0.01124 -0.0733 0.0246 0.7510 9.750 1.3306 0.01827 0.01175 -0.0727 0.0239 0.7534 10.000 1.3530 0.01893 0.01245 -0.0718 0.0231 0.7557 10.250 1.3747 0.01965 0.01323 -0.0708 0.0225 0.7581 10.500 1.3983 0.02011 0.01375 -0.0701 0.0221 0.7606 10.750 1.4210 0.02064 0.01435 -0.0693 0.0216 0.7629 11.000 1.4432 0.02122 0.01498 -0.0684 0.0212 0.7650 11.250 1.4648 0.02180 0.01562 -0.0675 0.0208 0.7675 11.500 1.4857 0.02240 0.01629 -0.0664 0.0204 0.7702 11.750 1.5055 0.02307 0.01703 -0.0652 0.0201 0.7728 12.000 1.5235 0.02390 0.01791 -0.0638 0.0197 0.7754 12.250 1.5376 0.02503 0.01911 -0.0618 0.0193 0.7782 12.500 1.5490 0.02634 0.02054 -0.0595 0.0190 0.7808 12.750 1.5655 0.02708 0.02136 -0.0579 0.0188 0.7834 13.000 1.5796 0.02788 0.02228 -0.0559 0.0187 0.7866 13.250 1.5910 0.02874 0.02324 -0.0535 0.0185 0.7897 13.500 1.5972 0.02969 0.02430 -0.0503 0.0183 0.7929 13.750 1.6046 0.03079 0.02550 -0.0476 0.0182 0.7962 14.000 1.6113 0.03200 0.02681 -0.0451 0.0180 0.7992 14.250 1.6170 0.03333 0.02826 -0.0426 0.0178 0.8029 14.500 1.6216 0.03480 0.02985 -0.0403 0.0177 0.8066 14.750 1.6250 0.03645 0.03162 -0.0382 0.0175 0.8105 15.000 1.6274 0.03829 0.03356 -0.0363 0.0174 0.8142 15.250 1.6283 0.04035 0.03574 -0.0346 0.0173 0.8179 15.500 1.6280 0.04264 0.03815 -0.0332 0.0172 0.8216 15.750 1.6265 0.04520 0.04084 -0.0322 0.0170 0.8255 16.000 1.6238 0.04805 0.04381 -0.0316 0.0169 0.8294 16.250 1.6193 0.05130 0.04718 -0.0313 0.0168 0.8331 16.500 1.6119 0.05512 0.05113 -0.0317 0.0167 0.8369 16.750 1.6026 0.05944 0.05559 -0.0326 0.0166 0.8410 17.000 1.5887 0.06480 0.06110 -0.0344 0.0166 0.8449 17.250 1.5715 0.07117 0.06763 -0.0372 0.0165 0.8484 17.500 1.5493 0.07894 0.07559 -0.0414 0.0165 0.8515 17.750 1.5223 0.08823 0.08507 -0.0468 0.0165 0.8543 18.000 1.4878 0.09930 0.09635 -0.0533 0.0165 0.8564