XFOIL Version 6.96 Calculated polar for: NACA 0012 AIRFOILS 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -1.1683 0.10069 0.09689 -0.0021 1.0000 0.0140 -17.500 -1.1891 0.09312 0.08920 -0.0060 1.0000 0.0141 -17.250 -1.2099 0.08573 0.08168 -0.0098 1.0000 0.0141 -17.000 -1.2297 0.07862 0.07444 -0.0135 1.0000 0.0142 -16.750 -1.2482 0.07193 0.06762 -0.0169 1.0000 0.0142 -16.500 -1.2642 0.06573 0.06129 -0.0201 1.0000 0.0143 -16.250 -1.2774 0.06009 0.05551 -0.0230 1.0000 0.0144 -16.000 -1.2876 0.05502 0.05031 -0.0256 1.0000 0.0145 -15.750 -1.2949 0.05052 0.04568 -0.0277 1.0000 0.0146 -15.500 -1.2995 0.04660 0.04164 -0.0294 1.0000 0.0148 -15.250 -1.3018 0.04316 0.03807 -0.0306 1.0000 0.0150 -15.000 -1.3021 0.04016 0.03496 -0.0314 1.0000 0.0152 -14.750 -1.3008 0.03755 0.03223 -0.0318 1.0000 0.0154 -14.500 -1.2982 0.03526 0.02983 -0.0317 1.0000 0.0156 -14.250 -1.2939 0.03328 0.02774 -0.0313 1.0000 0.0159 -14.000 -1.2885 0.03156 0.02589 -0.0305 1.0000 0.0162 -13.750 -1.2815 0.03007 0.02429 -0.0295 1.0000 0.0166 -13.500 -1.2731 0.02878 0.02288 -0.0282 1.0000 0.0169 -13.250 -1.2678 0.02736 0.02140 -0.0265 1.0000 0.0172 -13.000 -1.2593 0.02623 0.02021 -0.0247 1.0000 0.0176 -12.750 -1.2491 0.02528 0.01919 -0.0229 1.0000 0.0180 -12.500 -1.2378 0.02443 0.01826 -0.0209 1.0000 0.0185 -12.250 -1.2249 0.02365 0.01740 -0.0191 1.0000 0.0189 -12.000 -1.2093 0.02289 0.01656 -0.0176 1.0000 0.0195 -11.750 -1.1925 0.02217 0.01577 -0.0163 1.0000 0.0200 -11.500 -1.1753 0.02145 0.01497 -0.0150 1.0000 0.0205 -11.250 -1.1580 0.02071 0.01419 -0.0137 1.0000 0.0212 -11.000 -1.1389 0.02009 0.01353 -0.0126 1.0000 0.0220 -10.750 -1.1189 0.01952 0.01291 -0.0116 1.0000 0.0229 -10.500 -1.0984 0.01898 0.01231 -0.0106 1.0000 0.0238 -10.250 -1.0782 0.01842 0.01168 -0.0096 1.0000 0.0246 -10.000 -1.0580 0.01784 0.01108 -0.0085 1.0000 0.0256 -9.750 -1.0369 0.01734 0.01055 -0.0075 1.0000 0.0267 -9.500 -1.0154 0.01689 0.01006 -0.0066 1.0000 0.0280 -9.250 -0.9940 0.01644 0.00956 -0.0055 1.0000 0.0292 -9.000 -0.9731 0.01596 0.00908 -0.0045 1.0000 0.0308 -8.750 -0.9517 0.01556 0.00865 -0.0034 1.0000 0.0325 -8.500 -0.9302 0.01520 0.00824 -0.0023 1.0000 0.0340 -8.250 -0.9096 0.01477 0.00782 -0.0010 1.0000 0.0360 -8.000 -0.8883 0.01441 0.00745 0.0001 1.0000 0.0384 -7.750 -0.8670 0.01408 0.00709 0.0013 1.0000 0.0407 -7.500 -0.8461 0.01371 0.00674 0.0026 1.0000 0.0437 -7.250 -0.8248 0.01342 0.00643 0.0038 1.0000 0.0466 -7.000 -0.8039 0.01308 0.00611 0.0050 1.0000 0.0504 -6.750 -0.7799 0.01279 0.00582 0.0056 0.9995 0.0547 -6.500 -0.7471 0.01242 0.00548 0.0044 0.9969 0.0608 -6.250 -0.7137 0.01209 0.00517 0.0030 0.9945 0.0678 -6.000 -0.6812 0.01177 0.00488 0.0018 0.9914 0.0761 -5.750 -0.6486 0.01145 0.00460 0.0006 0.9878 0.0862 -5.500 -0.6149 0.01112 0.00433 -0.0008 0.9848 0.0986 -5.250 -0.5817 0.01079 0.00407 -0.0021 0.9814 0.1131 -5.000 -0.5512 0.01046 0.00382 -0.0028 0.9757 0.1296 -4.750 -0.5185 0.01014 0.00359 -0.0040 0.9711 0.1496 -4.500 -0.4888 0.00985 0.00338 -0.0044 0.9640 0.1702 -4.250 -0.4576 0.00953 0.00317 -0.0052 0.9573 0.1940 -4.000 -0.4287 0.00925 0.00298 -0.0055 0.9484 0.2186 -3.750 -0.3988 0.00897 0.00280 -0.0059 0.9395 0.2454 -3.500 -0.3711 0.00871 0.00264 -0.0058 0.9277 0.2713 -3.250 -0.3437 0.00847 0.00249 -0.0057 0.9150 0.2982 -3.000 -0.3166 0.00826 0.00234 -0.0054 0.9008 0.3257 -2.750 -0.2901 0.00806 0.00221 -0.0050 0.8850 0.3532 -2.500 -0.2637 0.00789 0.00210 -0.0045 0.8675 0.3801 -2.250 -0.2373 0.00774 0.00199 -0.0041 0.8486 0.4076 -2.000 -0.2111 0.00761 0.00189 -0.0036 0.8285 0.4342 -1.500 -0.1585 0.00741 0.00173 -0.0026 0.7855 0.4872 -1.250 -0.1321 0.00734 0.00167 -0.0022 0.7625 0.5131 -1.000 -0.1057 0.00729 0.00162 -0.0017 0.7391 0.5392 -0.750 -0.0793 0.00724 0.00158 -0.0013 0.7149 0.5648 -0.500 -0.0529 0.00722 0.00155 -0.0008 0.6905 0.5906 -0.250 -0.0265 0.00719 0.00154 -0.0004 0.6655 0.6157 0.000 0.0000 0.00720 0.00153 0.0000 0.6407 0.6407 0.250 0.0265 0.00719 0.00154 0.0004 0.6155 0.6656 0.500 0.0529 0.00722 0.00155 0.0008 0.5906 0.6906 0.750 0.0794 0.00724 0.00158 0.0013 0.5650 0.7147 1.000 0.1058 0.00729 0.00162 0.0017 0.5393 0.7390 1.250 0.1321 0.00734 0.00167 0.0022 0.5130 0.7625 1.500 0.1585 0.00741 0.00173 0.0026 0.4874 0.7855 1.750 0.1848 0.00751 0.00180 0.0031 0.4607 0.8076 2.000 0.2111 0.00761 0.00189 0.0036 0.4341 0.8285 2.250 0.2373 0.00774 0.00199 0.0041 0.4075 0.8487 2.500 0.2637 0.00789 0.00210 0.0045 0.3803 0.8676 2.750 0.2901 0.00806 0.00221 0.0050 0.3534 0.8850 3.000 0.3167 0.00826 0.00234 0.0054 0.3260 0.9008 3.250 0.3437 0.00848 0.00249 0.0057 0.2980 0.9150 3.500 0.3711 0.00871 0.00264 0.0058 0.2713 0.9277 3.750 0.3988 0.00897 0.00280 0.0059 0.2452 0.9395 4.000 0.4287 0.00925 0.00298 0.0055 0.2186 0.9484 4.250 0.4576 0.00953 0.00317 0.0052 0.1941 0.9573 4.500 0.4889 0.00985 0.00338 0.0044 0.1701 0.9640 4.750 0.5185 0.01014 0.00359 0.0040 0.1497 0.9711 5.000 0.5512 0.01046 0.00382 0.0028 0.1297 0.9757 5.250 0.5818 0.01079 0.00406 0.0021 0.1131 0.9814 5.500 0.6150 0.01112 0.00433 0.0008 0.0986 0.9848 5.750 0.6487 0.01145 0.00460 -0.0007 0.0862 0.9878 6.000 0.6813 0.01177 0.00488 -0.0018 0.0761 0.9914 6.250 0.7138 0.01209 0.00517 -0.0030 0.0678 0.9945 6.500 0.7472 0.01242 0.00548 -0.0044 0.0608 0.9969 6.750 0.7799 0.01279 0.00582 -0.0057 0.0547 0.9995 7.000 0.8038 0.01308 0.00611 -0.0050 0.0504 1.0000 7.250 0.8247 0.01342 0.00642 -0.0037 0.0467 1.0000 7.500 0.8461 0.01371 0.00674 -0.0025 0.0437 1.0000 7.750 0.8670 0.01408 0.00709 -0.0013 0.0407 1.0000 8.000 0.8883 0.01441 0.00745 -0.0001 0.0384 1.0000 8.250 0.9096 0.01477 0.00781 0.0010 0.0360 1.0000 8.500 0.9302 0.01520 0.00824 0.0023 0.0340 1.0000 8.750 0.9517 0.01556 0.00865 0.0034 0.0325 1.0000 9.000 0.9731 0.01596 0.00908 0.0045 0.0308 1.0000 9.250 0.9941 0.01644 0.00956 0.0055 0.0292 1.0000 9.500 1.0154 0.01689 0.01005 0.0066 0.0280 1.0000 9.750 1.0370 0.01734 0.01055 0.0075 0.0267 1.0000 10.000 1.0581 0.01783 0.01108 0.0085 0.0256 1.0000 10.250 1.0783 0.01842 0.01168 0.0095 0.0246 1.0000 10.500 1.0986 0.01898 0.01230 0.0106 0.0238 1.0000 10.750 1.1190 0.01952 0.01291 0.0116 0.0229 1.0000 11.000 1.1390 0.02009 0.01353 0.0126 0.0220 1.0000 11.250 1.1582 0.02071 0.01418 0.0137 0.0212 1.0000 11.500 1.1756 0.02145 0.01497 0.0150 0.0205 1.0000 11.750 1.1928 0.02217 0.01577 0.0163 0.0200 1.0000 12.000 1.2097 0.02289 0.01656 0.0176 0.0195 1.0000 12.250 1.2253 0.02365 0.01740 0.0190 0.0189 1.0000 12.500 1.2383 0.02443 0.01826 0.0208 0.0185 1.0000 12.750 1.2496 0.02528 0.01919 0.0228 0.0180 1.0000 13.000 1.2599 0.02623 0.02021 0.0246 0.0176 1.0000 13.250 1.2685 0.02736 0.02140 0.0264 0.0172 1.0000 13.500 1.2740 0.02877 0.02287 0.0281 0.0168 1.0000 13.750 1.2822 0.03007 0.02429 0.0293 0.0166 1.0000 14.000 1.2893 0.03156 0.02589 0.0304 0.0162 1.0000 14.250 1.2950 0.03327 0.02772 0.0311 0.0159 1.0000 14.500 1.2994 0.03524 0.02981 0.0316 0.0156 1.0000 14.750 1.3021 0.03752 0.03220 0.0316 0.0154 1.0000 15.000 1.3035 0.04013 0.03493 0.0312 0.0152 1.0000 15.250 1.3033 0.04311 0.03803 0.0304 0.0149 1.0000 15.500 1.3012 0.04654 0.04158 0.0292 0.0148 1.0000 15.750 1.2967 0.05047 0.04563 0.0275 0.0146 1.0000 16.000 1.2895 0.05495 0.05023 0.0253 0.0145 1.0000 16.250 1.2794 0.06003 0.05545 0.0228 0.0144 1.0000 16.500 1.2662 0.06567 0.06122 0.0199 0.0143 1.0000 16.750 1.2503 0.07187 0.06756 0.0166 0.0142 1.0000 17.000 1.2320 0.07855 0.07437 0.0132 0.0142 1.0000 17.250 1.2122 0.08566 0.08161 0.0095 0.0141 1.0000 17.500 1.1914 0.09306 0.08914 0.0057 0.0141 1.0000 17.750 1.1705 0.10066 0.09686 0.0018 0.0140 1.0000