XFOIL Version 6.96 Calculated polar for: NACA M12 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.5106 0.10070 0.09311 -0.0256 1.0000 0.0787 -9.750 -0.5138 0.09573 0.08818 -0.0282 1.0000 0.0775 -9.500 -0.5212 0.09001 0.08251 -0.0320 1.0000 0.0763 -9.250 -0.5371 0.08341 0.07594 -0.0369 1.0000 0.0749 -9.000 -0.5598 0.07779 0.07030 -0.0389 1.0000 0.0737 -8.750 -0.5791 0.07258 0.06498 -0.0396 1.0000 0.0728 -8.500 -0.5941 0.06782 0.06003 -0.0392 1.0000 0.0721 -8.250 -0.6021 0.06367 0.05566 -0.0380 1.0000 0.0717 -8.000 -0.6034 0.06025 0.05204 -0.0365 1.0000 0.0719 -7.750 -0.5994 0.05758 0.04924 -0.0349 1.0000 0.0729 -7.500 -0.5950 0.05504 0.04654 -0.0330 1.0000 0.0741 -7.250 -0.5904 0.05246 0.04372 -0.0309 1.0000 0.0754 -7.000 -0.5852 0.04981 0.04081 -0.0287 1.0000 0.0763 -6.750 -0.5786 0.04720 0.03791 -0.0264 1.0000 0.0769 -6.500 -0.5702 0.04473 0.03512 -0.0242 1.0000 0.0773 -6.250 -0.5601 0.04241 0.03249 -0.0219 1.0000 0.0780 -6.000 -0.5485 0.04023 0.02998 -0.0198 1.0000 0.0788 -5.750 -0.5352 0.03815 0.02755 -0.0178 1.0000 0.0799 -5.500 -0.5206 0.03636 0.02543 -0.0159 1.0000 0.0820 -5.250 -0.5051 0.03556 0.02460 -0.0143 1.0000 0.0843 -5.000 -0.4888 0.03453 0.02343 -0.0128 1.0000 0.0869 -4.750 -0.4713 0.03328 0.02195 -0.0113 1.0000 0.0895 -4.250 -0.4341 0.03124 0.01960 -0.0088 1.0000 0.0942 -4.000 -0.3997 0.03030 0.01849 -0.0104 0.9944 0.0992 -3.750 -0.3608 0.02962 0.01762 -0.0129 0.9862 0.1081 -3.500 -0.3221 0.02896 0.01670 -0.0152 0.9777 0.1199 -3.250 -0.2811 0.02810 0.01557 -0.0177 0.9704 0.1363 -3.000 -0.2437 0.02671 0.01408 -0.0197 0.9623 0.1591 -2.750 -0.2044 0.02472 0.01233 -0.0226 0.9568 0.1875 -2.500 -0.1750 0.02344 0.01168 -0.0240 0.9465 0.2188 -2.250 -0.1389 0.02290 0.01146 -0.0261 0.9372 0.3030 -2.000 -0.1067 0.02199 0.01117 -0.0275 0.9275 0.4029 -1.750 -0.0781 0.02103 0.01130 -0.0270 0.9182 0.6182 -1.500 -0.0236 0.02097 0.01162 -0.0306 0.9117 0.7858 -1.250 0.0257 0.02109 0.01165 -0.0341 0.9030 0.8543 -1.000 0.0703 0.02118 0.01160 -0.0370 0.8931 0.8920 -0.750 0.1119 0.02129 0.01158 -0.0395 0.8818 0.9199 -0.500 0.1556 0.02130 0.01145 -0.0424 0.8720 0.9377 -0.250 0.1948 0.02134 0.01140 -0.0446 0.8595 0.9522 0.000 0.2347 0.02138 0.01135 -0.0469 0.8469 0.9661 0.250 0.2773 0.02137 0.01125 -0.0497 0.8353 0.9792 0.500 0.3209 0.02131 0.01113 -0.0527 0.8235 0.9915 0.750 0.3571 0.02134 0.01111 -0.0545 0.8094 1.0000 1.000 0.3800 0.02144 0.01115 -0.0534 0.7951 1.0000 1.250 0.4031 0.02153 0.01120 -0.0524 0.7813 1.0000 1.500 0.4271 0.02161 0.01122 -0.0514 0.7683 1.0000 1.750 0.4510 0.02169 0.01126 -0.0505 0.7553 1.0000 2.000 0.4726 0.02188 0.01143 -0.0492 0.7409 1.0000 2.250 0.4947 0.02207 0.01160 -0.0480 0.7270 1.0000 2.500 0.5175 0.02223 0.01175 -0.0469 0.7138 1.0000 2.750 0.5416 0.02235 0.01185 -0.0458 0.7014 1.0000 3.000 0.5639 0.02254 0.01205 -0.0446 0.6878 1.0000 3.250 0.5851 0.02281 0.01233 -0.0433 0.6736 1.0000 3.500 0.6069 0.02305 0.01261 -0.0420 0.6598 1.0000 3.750 0.6294 0.02327 0.01283 -0.0408 0.6464 1.0000 4.000 0.6527 0.02344 0.01301 -0.0396 0.6332 1.0000 4.250 0.6753 0.02364 0.01324 -0.0383 0.6193 1.0000 4.500 0.6963 0.02392 0.01356 -0.0369 0.6041 1.0000 4.750 0.7174 0.02418 0.01387 -0.0354 0.5888 1.0000 5.000 0.7388 0.02444 0.01416 -0.0340 0.5731 1.0000 5.250 0.7601 0.02470 0.01448 -0.0325 0.5572 1.0000 5.500 0.7814 0.02497 0.01480 -0.0310 0.5412 1.0000 5.750 0.8025 0.02527 0.01515 -0.0296 0.5248 1.0000 6.000 0.8234 0.02559 0.01554 -0.0281 0.5081 1.0000 6.250 0.8440 0.02592 0.01593 -0.0266 0.4907 1.0000 6.500 0.8642 0.02626 0.01633 -0.0250 0.4724 1.0000 6.750 0.8841 0.02658 0.01668 -0.0233 0.4530 1.0000 7.000 0.9015 0.02693 0.01709 -0.0213 0.4302 1.0000 7.250 0.9168 0.02728 0.01743 -0.0190 0.4034 1.0000 7.500 0.9299 0.02772 0.01786 -0.0165 0.3739 1.0000 7.750 0.9423 0.02827 0.01835 -0.0140 0.3439 1.0000 8.000 0.9539 0.02895 0.01896 -0.0115 0.3144 1.0000 8.250 0.9638 0.02978 0.01973 -0.0090 0.2847 1.0000 8.500 0.9721 0.03080 0.02066 -0.0065 0.2551 1.0000 8.750 0.9783 0.03201 0.02177 -0.0039 0.2261 1.0000 9.000 0.9830 0.03342 0.02304 -0.0012 0.2006 1.0000 9.250 0.9853 0.03495 0.02446 0.0016 0.1792 1.0000 9.500 0.9870 0.03662 0.02603 0.0042 0.1619 1.0000 10.000 0.9952 0.04020 0.02957 0.0084 0.1355 1.0000 10.250 1.0002 0.04206 0.03138 0.0101 0.1261 1.0000 10.500 1.0071 0.04390 0.03327 0.0115 0.1174 1.0000 10.750 1.0167 0.04572 0.03513 0.0129 0.1110 1.0000 11.000 1.0270 0.04755 0.03706 0.0141 0.1047 1.0000 11.250 1.0372 0.04935 0.03880 0.0152 0.0995 1.0000 11.500 1.0466 0.05144 0.04120 0.0163 0.0943 1.0000 11.750 1.0573 0.05342 0.04326 0.0172 0.0901 1.0000 12.000 1.0712 0.05529 0.04508 0.0182 0.0864 1.0000 12.250 1.0736 0.05812 0.04827 0.0190 0.0830 1.0000 12.500 1.0755 0.06093 0.05132 0.0196 0.0799 1.0000 12.750 1.0793 0.06361 0.05412 0.0202 0.0773 1.0000 13.000 1.0925 0.06569 0.05616 0.0209 0.0744 1.0000 13.250 1.0815 0.06989 0.06069 0.0208 0.0730 1.0000 13.500 1.0671 0.07467 0.06581 0.0201 0.0718 1.0000 13.750 1.0496 0.08008 0.07152 0.0186 0.0708 1.0000 14.000 1.0280 0.08643 0.07814 0.0162 0.0702 1.0000 14.250 1.0003 0.09425 0.08619 0.0125 0.0701 1.0000 14.500 0.9640 0.10446 0.09663 0.0069 0.0707 1.0000 14.750 0.9186 0.11819 0.11054 -0.0012 0.0717 1.0000