XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0612 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -1.0317 0.10278 0.09919 -0.0339 1.0000 0.0178 -18.000 -1.0651 0.09220 0.08842 -0.0400 1.0000 0.0178 -17.750 -1.0900 0.08343 0.07948 -0.0451 1.0000 0.0178 -17.500 -1.1089 0.07603 0.07191 -0.0494 1.0000 0.0178 -17.250 -1.1231 0.06967 0.06541 -0.0532 1.0000 0.0179 -17.000 -1.1339 0.06420 0.05979 -0.0562 1.0000 0.0180 -16.750 -1.1417 0.05947 0.05492 -0.0587 1.0000 0.0181 -16.500 -1.1470 0.05535 0.05067 -0.0607 1.0000 0.0182 -16.250 -1.1505 0.05171 0.04690 -0.0623 1.0000 0.0184 -16.000 -1.1522 0.04850 0.04358 -0.0634 1.0000 0.0185 -15.750 -1.1527 0.04564 0.04060 -0.0642 1.0000 0.0187 -15.500 -1.1514 0.04306 0.03791 -0.0647 1.0000 0.0189 -15.250 -1.1488 0.04074 0.03548 -0.0650 1.0000 0.0190 -15.000 -1.1448 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-0.0881 0.9663 0.0746 -5.500 -0.2533 0.01097 0.00449 -0.0893 0.9640 0.0819 -5.250 -0.2199 0.01071 0.00427 -0.0908 0.9619 0.0915 -5.000 -0.1858 0.01042 0.00406 -0.0924 0.9601 0.1039 -4.750 -0.1513 0.01012 0.00384 -0.0941 0.9586 0.1215 -4.500 -0.1163 0.00979 0.00364 -0.0960 0.9572 0.1475 -4.250 -0.0805 0.00941 0.00342 -0.0981 0.9560 0.1851 -4.000 -0.0463 0.00896 0.00322 -0.1001 0.9531 0.2443 -3.750 -0.0106 0.00845 0.00301 -0.1024 0.9503 0.3179 -3.500 0.0265 0.00793 0.00278 -0.1050 0.9479 0.3948 -3.250 0.0646 0.00739 0.00264 -0.1078 0.9460 0.4968 -3.000 0.0987 0.00722 0.00265 -0.1092 0.9433 0.5509 -2.750 0.1309 0.00717 0.00267 -0.1100 0.9397 0.5787 -2.500 0.1605 0.00715 0.00268 -0.1101 0.9326 0.5974 -2.250 0.1918 0.00712 0.00268 -0.1106 0.9269 0.6119 -2.000 0.2209 0.00713 0.00270 -0.1105 0.9173 0.6246 -1.750 0.2499 0.00714 0.00268 -0.1103 0.9020 0.6369 -1.500 0.2779 0.00717 0.00270 -0.1099 0.8831 0.6446 -1.250 0.3064 0.00721 0.00266 -0.1096 0.8605 0.6506 -1.000 0.3345 0.00730 0.00260 -0.1092 0.8267 0.6550 -0.750 0.3616 0.00743 0.00261 -0.1087 0.7877 0.6579 -0.500 0.3879 0.00768 0.00262 -0.1080 0.7331 0.6606 -0.250 0.4132 0.00807 0.00268 -0.1072 0.6556 0.6633 0.000 0.4361 0.00879 0.00286 -0.1062 0.5356 0.6658 0.250 0.4600 0.00953 0.00308 -0.1056 0.4197 0.6682 0.500 0.4857 0.01012 0.00328 -0.1053 0.3305 0.6707 0.750 0.5118 0.01060 0.00347 -0.1051 0.2606 0.6727 1.000 0.5382 0.01101 0.00366 -0.1048 0.2090 0.6746 1.250 0.5652 0.01137 0.00385 -0.1046 0.1673 0.6766 1.500 0.5923 0.01171 0.00405 -0.1045 0.1356 0.6787 1.750 0.6199 0.01198 0.00423 -0.1044 0.1163 0.6807 2.000 0.6477 0.01223 0.00441 -0.1044 0.1016 0.6826 2.250 0.6754 0.01250 0.00460 -0.1043 0.0889 0.6845 2.500 0.7032 0.01275 0.00479 -0.1043 0.0798 0.6864 2.750 0.7309 0.01302 0.00499 -0.1042 0.0727 0.6882 3.000 0.7587 0.01323 0.00520 -0.1041 0.0684 0.6899 3.250 0.7859 0.01347 0.00543 -0.1039 0.0642 0.6915 3.500 0.8131 0.01372 0.00569 -0.1037 0.0612 0.6933 3.750 0.8403 0.01396 0.00595 -0.1035 0.0583 0.6954 4.000 0.8671 0.01425 0.00622 -0.1032 0.0552 0.6977 4.250 0.8941 0.01453 0.00650 -0.1030 0.0527 0.6999 4.500 0.9211 0.01479 0.00678 -0.1027 0.0503 0.7020 4.750 0.9479 0.01509 0.00707 -0.1025 0.0477 0.7040 5.000 0.9745 0.01540 0.00738 -0.1022 0.0453 0.7059 5.500 1.0273 0.01600 0.00799 -0.1016 0.0403 0.7095 5.750 1.0532 0.01631 0.00835 -0.1011 0.0382 0.7115 6.000 1.0790 0.01664 0.00870 -0.1007 0.0361 0.7135 6.250 1.1044 0.01702 0.00908 -0.1002 0.0342 0.7155 6.500 1.1299 0.01738 0.00948 -0.0997 0.0325 0.7175 6.750 1.1551 0.01776 0.00988 -0.0991 0.0309 0.7196 7.000 1.1798 0.01820 0.01032 -0.0986 0.0295 0.7218 7.250 1.2045 0.01865 0.01081 -0.0979 0.0285 0.7239 7.500 1.2289 0.01910 0.01130 -0.0973 0.0276 0.7259 7.750 1.2529 0.01956 0.01180 -0.0966 0.0266 0.7277 8.000 1.2762 0.02006 0.01235 -0.0957 0.0258 0.7296 8.250 1.2985 0.02067 0.01299 -0.0948 0.0250 0.7317 8.500 1.3212 0.02121 0.01361 -0.0938 0.0245 0.7340 8.750 1.3436 0.02176 0.01424 -0.0929 0.0239 0.7364 9.000 1.3657 0.02233 0.01487 -0.0919 0.0232 0.7388 9.250 1.3874 0.02292 0.01551 -0.0908 0.0226 0.7412 9.500 1.4084 0.02354 0.01618 -0.0897 0.0221 0.7435 9.750 1.4282 0.02425 0.01694 -0.0884 0.0216 0.7458 10.000 1.4459 0.02510 0.01786 -0.0868 0.0211 0.7479 10.250 1.4645 0.02582 0.01868 -0.0853 0.0208 0.7502 10.500 1.4824 0.02657 0.01953 -0.0837 0.0205 0.7525 10.750 1.4992 0.02736 0.02043 -0.0819 0.0202 0.7549 11.000 1.5146 0.02818 0.02135 -0.0800 0.0198 0.7574 11.250 1.5285 0.02904 0.02230 -0.0778 0.0195 0.7599 11.500 1.5389 0.02992 0.02327 -0.0751 0.0193 0.7624 11.750 1.5486 0.03085 0.02431 -0.0723 0.0190 0.7645 12.000 1.5585 0.03187 0.02544 -0.0697 0.0188 0.7668 12.250 1.5679 0.03296 0.02664 -0.0673 0.0185 0.7692 12.500 1.5760 0.03417 0.02794 -0.0648 0.0183 0.7718 12.750 1.5827 0.03551 0.02938 -0.0623 0.0181 0.7745 13.000 1.5876 0.03703 0.03100 -0.0598 0.0180 0.7771 13.250 1.5904 0.03878 0.03285 -0.0573 0.0178 0.7796 13.500 1.5900 0.04084 0.03504 -0.0547 0.0176 0.7818 13.750 1.5917 0.04282 0.03717 -0.0526 0.0175 0.7840 14.000 1.5929 0.04493 0.03945 -0.0508 0.0174 0.7864 14.250 1.5927 0.04727 0.04195 -0.0491 0.0172 0.7891 14.500 1.5909 0.04991 0.04475 -0.0478 0.0171 0.7918 14.750 1.5870 0.05291 0.04791 -0.0468 0.0170 0.7945 15.000 1.5810 0.05633 0.05150 -0.0462 0.0168 0.7970 15.250 1.5732 0.06021 0.05556 -0.0462 0.0167 0.7991 15.500 1.5626 0.06474 0.06027 -0.0469 0.0166 0.8013 15.750 1.5488 0.07013 0.06586 -0.0484 0.0165 0.8035 16.000 1.5317 0.07663 0.07256 -0.0512 0.0165 0.8056 16.250 1.5099 0.08467 0.08081 -0.0555 0.0164 0.8076 16.500 1.4817 0.09461 0.09097 -0.0614 0.0164 0.8090 16.750 1.4446 0.10699 0.10360 -0.0691 0.0165 0.8099 17.000 1.3970 0.12190 0.11876 -0.0783 0.0165 0.8100 17.250 1.3325 0.14118 0.13831 -0.0906 0.0167 0.8091