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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0935 0.10266 0.09984 -0.0343 1.0000 0.0178 -18.750 -1.1235 0.09302 0.09005 -0.0398 1.0000 0.0178 -18.500 -1.1475 0.08463 0.08151 -0.0446 1.0000 0.0178 -18.250 -1.1660 0.07748 0.07422 -0.0488 1.0000 0.0179 -18.000 -1.1808 0.07110 0.06770 -0.0525 1.0000 0.0179 -17.750 -1.1921 0.06555 0.06203 -0.0556 1.0000 0.0180 -17.500 -1.2008 0.06065 0.05701 -0.0582 1.0000 0.0181 -17.250 -1.2070 0.05633 0.05257 -0.0603 1.0000 0.0182 -17.000 -1.2112 0.05251 0.04864 -0.0620 1.0000 0.0183 -16.750 -1.2136 0.04908 0.04511 -0.0634 1.0000 0.0184 -16.500 -1.2146 0.04603 0.04195 -0.0644 1.0000 0.0185 -16.250 -1.2142 0.04331 0.03914 -0.0651 1.0000 0.0187 -16.000 -1.2123 0.04084 0.03658 -0.0656 1.0000 0.0188 -15.750 -1.2090 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0.00455 -0.0895 0.9824 0.0646 -6.250 -0.3343 0.00980 0.00436 -0.0904 0.9803 0.0673 -6.000 -0.3009 0.00954 0.00413 -0.0919 0.9785 0.0715 -5.750 -0.2662 0.00929 0.00392 -0.0936 0.9773 0.0769 -5.500 -0.2311 0.00903 0.00371 -0.0954 0.9762 0.0848 -5.250 -0.1960 0.00877 0.00351 -0.0972 0.9750 0.0967 -5.000 -0.1604 0.00845 0.00330 -0.0991 0.9739 0.1190 -4.750 -0.1235 0.00802 0.00308 -0.1015 0.9730 0.1605 -4.500 -0.0859 0.00752 0.00284 -0.1042 0.9720 0.2222 -4.250 -0.0474 0.00695 0.00260 -0.1071 0.9710 0.3044 -4.000 -0.0085 0.00636 0.00235 -0.1102 0.9700 0.3993 -3.750 0.0286 0.00575 0.00215 -0.1127 0.9670 0.5166 -3.500 0.0606 0.00557 0.00211 -0.1136 0.9621 0.5635 -3.250 0.0918 0.00550 0.00207 -0.1141 0.9580 0.5845 -3.000 0.1219 0.00547 0.00205 -0.1144 0.9532 0.5968 -2.750 0.1503 0.00544 0.00200 -0.1142 0.9454 0.6063 -2.500 0.1784 0.00540 0.00197 -0.1139 0.9353 0.6144 -2.250 0.2068 0.00540 0.00192 -0.1136 0.9249 0.6231 -2.000 0.2352 0.00541 0.00194 -0.1134 0.9136 0.6311 -1.750 0.2637 0.00545 0.00192 -0.1132 0.8994 0.6381 -1.500 0.2921 0.00547 0.00194 -0.1130 0.8847 0.6442 -1.250 0.3208 0.00556 0.00200 -0.1129 0.8705 0.6516 -1.000 0.3493 0.00564 0.00203 -0.1127 0.8527 0.6579 -0.750 0.3776 0.00574 0.00208 -0.1125 0.8338 0.6620 -0.500 0.4061 0.00584 0.00211 -0.1124 0.8104 0.6651 -0.250 0.4341 0.00599 0.00215 -0.1121 0.7786 0.6683 0.000 0.4615 0.00624 0.00220 -0.1118 0.7328 0.6708 0.250 0.4864 0.00670 0.00228 -0.1111 0.6376 0.6736 0.500 0.5090 0.00756 0.00253 -0.1101 0.4886 0.6759 0.750 0.5334 0.00830 0.00277 -0.1096 0.3693 0.6779 1.000 0.5588 0.00890 0.00298 -0.1092 0.2760 0.6798 1.250 0.5852 0.00938 0.00318 -0.1090 0.2094 0.6817 1.500 0.6119 0.00981 0.00337 -0.1088 0.1573 0.6838 1.750 0.6392 0.01017 0.00355 -0.1087 0.1221 0.6859 2.000 0.6669 0.01047 0.00373 -0.1086 0.0991 0.6878 2.250 0.6947 0.01075 0.00391 -0.1085 0.0846 0.6893 2.500 0.7228 0.01090 0.00405 -0.1085 0.0782 0.6919 2.750 0.7505 0.01114 0.00425 -0.1084 0.0720 0.6939 3.000 0.7786 0.01130 0.00443 -0.1083 0.0687 0.6957 3.250 0.8063 0.01154 0.00463 -0.1082 0.0646 0.6975 3.500 0.8339 0.01177 0.00485 -0.1080 0.0616 0.6993 3.750 0.8618 0.01195 0.00504 -0.1079 0.0593 0.7012 4.000 0.8893 0.01219 0.00526 -0.1078 0.0563 0.7030 4.250 0.9165 0.01246 0.00552 -0.1076 0.0532 0.7048 4.500 0.9443 0.01265 0.00571 -0.1074 0.0510 0.7064 4.750 0.9714 0.01291 0.00594 -0.1072 0.0482 0.7081 5.000 0.9984 0.01316 0.00620 -0.1070 0.0454 0.7107 5.250 1.0257 0.01334 0.00640 -0.1068 0.0428 0.7129 5.500 1.0519 0.01368 0.00672 -0.1064 0.0397 0.7150 5.750 1.0789 0.01389 0.00695 -0.1061 0.0377 0.7171 6.000 1.1052 0.01420 0.00724 -0.1058 0.0354 0.7192 6.250 1.1312 0.01456 0.00761 -0.1053 0.0336 0.7212 6.500 1.1574 0.01485 0.00791 -0.1049 0.0321 0.7233 6.750 1.1832 0.01521 0.00826 -0.1045 0.0307 0.7252 7.000 1.2078 0.01571 0.00877 -0.1038 0.0292 0.7270 7.250 1.2335 0.01601 0.00912 -0.1033 0.0284 0.7296 7.500 1.2588 0.01635 0.00950 -0.1028 0.0275 0.7318 7.750 1.2836 0.01674 0.00991 -0.1022 0.0265 0.7339 8.000 1.3072 0.01727 0.01046 -0.1013 0.0255 0.7360 8.250 1.3300 0.01789 0.01113 -0.1004 0.0248 0.7381 8.500 1.3542 0.01830 0.01159 -0.0996 0.0243 0.7403 8.750 1.3779 0.01876 0.01209 -0.0988 0.0238 0.7424 9.000 1.4012 0.01925 0.01262 -0.0980 0.0232 0.7442 9.250 1.4240 0.01974 0.01315 -0.0971 0.0227 0.7464 9.500 1.4461 0.02028 0.01374 -0.0961 0.0223 0.7489 9.750 1.4664 0.02098 0.01449 -0.0947 0.0217 0.7512 10.000 1.4825 0.02211 0.01570 -0.0928 0.0211 0.7536 10.250 1.5028 0.02274 0.01640 -0.0915 0.0209 0.7561 10.500 1.5231 0.02332 0.01706 -0.0902 0.0207 0.7585 10.750 1.5425 0.02397 0.01778 -0.0887 0.0204 0.7609 11.000 1.5608 0.02467 0.01855 -0.0871 0.0201 0.7629 11.250 1.5780 0.02538 0.01935 -0.0854 0.0198 0.7656 11.500 1.5939 0.02611 0.02016 -0.0834 0.0195 0.7681 11.750 1.6088 0.02681 0.02094 -0.0813 0.0192 0.7705 12.000 1.6217 0.02756 0.02175 -0.0789 0.0189 0.7730 12.250 1.6300 0.02837 0.02263 -0.0758 0.0187 0.7756 12.500 1.6393 0.02933 0.02365 -0.0729 0.0185 0.7781 12.750 1.6471 0.03044 0.02483 -0.0701 0.0183 0.7802 13.000 1.6524 0.03177 0.02626 -0.0671 0.0181 0.7831 13.250 1.6538 0.03345 0.02806 -0.0638 0.0179 0.7857 13.500 1.6480 0.03581 0.03059 -0.0601 0.0176 0.7881 13.750 1.6483 0.03775 0.03266 -0.0573 0.0175 0.7907 14.000 1.6528 0.03934 0.03437 -0.0551 0.0174 0.7934 14.250 1.6564 0.04109 0.03623 -0.0530 0.0174 0.7959 14.500 1.6581 0.04309 0.03835 -0.0511 0.0173 0.7984 14.750 1.6577 0.04535 0.04076 -0.0494 0.0172 0.8011 15.000 1.6559 0.04789 0.04344 -0.0479 0.0171 0.8038 15.250 1.6524 0.05076 0.04644 -0.0467 0.0170 0.8064 15.500 1.6464 0.05406 0.04988 -0.0459 0.0169 0.8090 15.750 1.6388 0.05779 0.05375 -0.0457 0.0168 0.8115 16.000 1.6287 0.06213 0.05823 -0.0460 0.0167 0.8136 16.250 1.6154 0.06723 0.06350 -0.0472 0.0167 0.8161 16.500 1.5994 0.07326 0.06971 -0.0494 0.0166 0.8183 16.750 1.5797 0.08050 0.07713 -0.0528 0.0166 0.8203 17.000 1.5561 0.08898 0.08580 -0.0575 0.0166 0.8221 17.250 1.5257 0.09934 0.09636 -0.0636 0.0166 0.8234 17.500 1.4878 0.11156 0.10880 -0.0711 0.0166 0.8242 17.750 1.4409 0.12597 0.12342 -0.0801 0.0167 0.8244 18.000 1.3801 0.14414 0.14184 -0.0920 0.0168 0.8237