XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0710 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.7054 0.08055 0.07637 -0.0449 1.0000 0.0230 -12.500 -0.7827 0.06129 0.05681 -0.0588 1.0000 0.0222 -12.250 -0.8175 0.05471 0.05001 -0.0611 1.0000 0.0221 -12.000 -0.8456 0.05042 0.04554 -0.0603 1.0000 0.0221 -11.750 -0.8713 0.04740 0.04237 -0.0575 1.0000 0.0222 -11.500 -0.8860 0.04383 0.03855 -0.0568 1.0000 0.0224 -11.250 -0.8913 0.04034 0.03472 -0.0566 1.0000 0.0227 -11.000 -0.8890 0.03708 0.03108 -0.0563 1.0000 0.0231 -10.750 -0.8800 0.03419 0.02779 -0.0561 1.0000 0.0234 -10.500 -0.8660 0.03175 0.02497 -0.0560 1.0000 0.0239 -10.250 -0.8489 0.02985 0.02284 -0.0559 1.0000 0.0243 -10.000 -0.8295 0.02853 0.02143 -0.0557 1.0000 0.0248 -9.750 -0.8088 0.02739 0.02019 -0.0557 1.0000 0.0254 -9.500 -0.7871 0.02628 0.01895 -0.0556 1.0000 0.0261 -9.250 -0.7647 0.02516 0.01769 -0.0556 1.0000 0.0270 -9.000 -0.7414 0.02413 0.01648 -0.0556 1.0000 0.0283 -8.750 -0.7175 0.02314 0.01530 -0.0556 1.0000 0.0296 -8.500 -0.6933 0.02226 0.01444 -0.0559 1.0000 0.0308 -8.250 -0.6683 0.02152 0.01365 -0.0561 1.0000 0.0321 -8.000 -0.6428 0.02076 0.01279 -0.0563 1.0000 0.0338 -7.750 -0.6166 0.02005 0.01196 -0.0565 1.0000 0.0355 -7.500 -0.5893 0.01930 0.01123 -0.0573 1.0000 0.0375 -7.250 -0.5620 0.01884 0.01074 -0.0578 1.0000 0.0402 -7.000 -0.5313 0.01837 0.01017 -0.0589 0.9993 0.0432 -6.750 -0.4986 0.01775 0.00960 -0.0607 0.9985 0.0466 -6.500 -0.4660 0.01735 0.00914 -0.0622 0.9975 0.0507 -6.250 -0.4326 0.01683 0.00864 -0.0640 0.9967 0.0551 -6.000 -0.3994 0.01646 0.00826 -0.0657 0.9958 0.0604 -5.750 -0.3651 0.01602 0.00781 -0.0676 0.9951 0.0661 -5.500 -0.3307 0.01568 0.00746 -0.0695 0.9943 0.0739 -5.250 -0.2962 0.01528 0.00713 -0.0714 0.9937 0.0835 -5.000 -0.2626 0.01495 0.00683 -0.0732 0.9928 0.0981 -4.750 -0.2283 0.01457 0.00657 -0.0751 0.9920 0.1215 -4.500 -0.1927 0.01414 0.00635 -0.0775 0.9915 0.1661 -4.250 -0.1535 0.01348 0.00611 -0.0810 0.9916 0.2595 -4.000 -0.1086 0.01254 0.00596 -0.0860 0.9931 0.4364 -3.750 -0.0759 0.01239 0.00638 -0.0871 0.9921 0.5687 -3.500 -0.0461 0.01253 0.00659 -0.0873 0.9901 0.6064 -3.250 -0.0148 0.01268 0.00674 -0.0880 0.9882 0.6299 -3.000 0.0159 0.01290 0.00698 -0.0884 0.9863 0.6499 -2.750 0.0468 0.01318 0.00727 -0.0888 0.9845 0.6675 -2.500 0.0758 0.01343 0.00754 -0.0888 0.9817 0.6816 -2.250 0.1046 0.01362 0.00774 -0.0888 0.9783 0.6910 -2.000 0.1345 0.01381 0.00795 -0.0891 0.9756 0.6983 -1.750 0.1663 0.01398 0.00814 -0.0897 0.9734 0.7054 -1.500 0.2021 0.01405 0.00821 -0.0914 0.9713 0.7117 -1.250 0.2284 0.01413 0.00834 -0.0908 0.9655 0.7152 -1.000 0.2657 0.01406 0.00830 -0.0926 0.9608 0.7190 -0.750 0.3041 0.01386 0.00814 -0.0946 0.9539 0.7230 -0.500 0.3579 0.01326 0.00754 -0.0995 0.9442 0.7266 -0.250 0.4028 0.01256 0.00690 -0.1019 0.9267 0.7281 0.250 0.4740 0.01181 0.00622 -0.1035 0.8784 0.7318 0.500 0.5127 0.01152 0.00592 -0.1050 0.8347 0.7342 0.750 0.5461 0.01213 0.00542 -0.1047 0.5938 0.7366 1.000 0.5619 0.01347 0.00579 -0.1025 0.3996 0.7397 1.500 0.6063 0.01520 0.00647 -0.1009 0.1790 0.7446 1.750 0.6302 0.01577 0.00681 -0.1002 0.1289 0.7467 2.000 0.6555 0.01623 0.00715 -0.0997 0.1035 0.7490 2.250 0.6818 0.01664 0.00751 -0.0994 0.0875 0.7514 2.500 0.7088 0.01704 0.00787 -0.0993 0.0767 0.7540 2.750 0.7362 0.01751 0.00827 -0.0994 0.0689 0.7568 3.000 0.7634 0.01788 0.00868 -0.0993 0.0629 0.7591 3.250 0.7878 0.01842 0.00919 -0.0986 0.0577 0.7607 3.500 0.8134 0.01882 0.00967 -0.0981 0.0535 0.7625 3.750 0.8386 0.01929 0.01013 -0.0976 0.0494 0.7646 4.000 0.8637 0.01984 0.01073 -0.0971 0.0460 0.7672 4.250 0.8898 0.02033 0.01126 -0.0968 0.0427 0.7700 4.500 0.9159 0.02095 0.01187 -0.0966 0.0402 0.7732 4.750 0.9405 0.02163 0.01262 -0.0959 0.0378 0.7754 5.000 0.9647 0.02221 0.01329 -0.0952 0.0354 0.7773 5.250 0.9888 0.02280 0.01390 -0.0946 0.0334 0.7793 5.500 1.0126 0.02368 0.01484 -0.0938 0.0318 0.7815 5.750 1.0371 0.02456 0.01585 -0.0932 0.0303 0.7838 6.000 1.0618 0.02546 0.01686 -0.0927 0.0290 0.7864 6.250 1.0867 0.02637 0.01783 -0.0923 0.0280 0.7892 6.500 1.1094 0.02733 0.01884 -0.0915 0.0271 0.7911 6.750 1.1315 0.02859 0.02025 -0.0905 0.0263 0.7929 7.000 1.1539 0.02985 0.02177 -0.0895 0.0254 0.7951 7.250 1.1756 0.03111 0.02326 -0.0885 0.0243 0.7976 7.500 1.1969 0.03232 0.02466 -0.0875 0.0235 0.8005 7.750 1.2177 0.03366 0.02617 -0.0866 0.0230 0.8034 8.000 1.2372 0.03497 0.02763 -0.0855 0.0225 0.8059 8.250 1.2545 0.03639 0.02920 -0.0840 0.0221 0.8078 8.500 1.2694 0.03832 0.03133 -0.0822 0.0218 0.8099 8.750 1.2795 0.04108 0.03458 -0.0798 0.0214 0.8124 9.000 1.2841 0.04443 0.03844 -0.0768 0.0211 0.8151 9.250 1.2816 0.04845 0.04299 -0.0732 0.0208 0.8178 9.500 1.2708 0.05301 0.04806 -0.0691 0.0206 0.8204 9.750 1.2491 0.05758 0.05307 -0.0640 0.0205 0.8222 10.000 1.2203 0.06218 0.05803 -0.0588 0.0204 0.8243 10.250 1.1868 0.06799 0.06419 -0.0556 0.0204 0.8263 10.500 1.1477 0.07549 0.07201 -0.0554 0.0205 0.8282 10.750 1.1027 0.08638 0.08319 -0.0609 0.0207 0.8298