XFOIL Version 6.96 Calculated polar for: GOE 612 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.7014 0.09230 0.08977 -0.0760 1.0000 0.0239 -16.750 -0.7425 0.08226 0.07958 -0.0820 1.0000 0.0240 -16.500 -0.7751 0.07418 0.07139 -0.0868 1.0000 0.0240 -16.000 -0.8261 0.05920 0.05616 -0.0980 0.9871 0.0242 -15.750 -0.8422 0.05178 0.04860 -0.1058 0.9807 0.0243 -15.500 -0.8528 0.04466 0.04133 -0.1142 0.9743 0.0243 -15.250 -0.8493 0.03840 0.03491 -0.1234 0.9704 0.0244 -15.000 -0.8364 0.03267 0.02900 -0.1333 0.9656 0.0245 -14.750 -0.8169 0.02765 0.02378 -0.1436 0.9584 0.0246 -14.500 -0.8090 0.02517 0.02113 -0.1466 0.9478 0.0247 -14.250 -0.8054 0.02380 0.01963 -0.1457 0.9385 0.0247 -14.000 -0.8046 0.02281 0.01854 -0.1430 0.9294 0.0248 -13.750 -0.8065 0.02186 0.01749 -0.1395 0.9214 0.0249 -13.500 -0.8003 0.02095 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0.0445 -3.500 0.1471 0.00908 0.00245 -0.1088 0.6271 0.0474 -3.250 0.1746 0.00897 0.00235 -0.1085 0.6224 0.0508 -3.000 0.2015 0.00888 0.00226 -0.1082 0.6164 0.0552 -2.750 0.2278 0.00880 0.00217 -0.1077 0.6104 0.0622 -2.500 0.2547 0.00864 0.00209 -0.1074 0.6057 0.0780 -2.250 0.2815 0.00854 0.00203 -0.1071 0.5997 0.0929 -2.000 0.3079 0.00851 0.00199 -0.1066 0.5928 0.1013 -1.750 0.3352 0.00845 0.00194 -0.1064 0.5866 0.1081 -1.500 0.3620 0.00842 0.00191 -0.1060 0.5799 0.1143 -1.250 0.3886 0.00839 0.00188 -0.1056 0.5746 0.1216 -0.750 0.4421 0.00827 0.00183 -0.1049 0.5626 0.1489 -0.500 0.4678 0.00818 0.00181 -0.1044 0.5556 0.1782 -0.250 0.4934 0.00808 0.00181 -0.1038 0.5470 0.2150 0.000 0.5187 0.00804 0.00183 -0.1033 0.5386 0.2442 0.250 0.5445 0.00802 0.00185 -0.1027 0.5292 0.2689 0.500 0.5700 0.00805 0.00188 -0.1021 0.5190 0.2867 0.750 0.5946 0.00812 0.00193 -0.1014 0.5048 0.3004 1.000 0.6186 0.00821 0.00198 -0.1005 0.4870 0.3128 1.250 0.6415 0.00837 0.00206 -0.0995 0.4644 0.3247 1.500 0.6630 0.00857 0.00218 -0.0982 0.4395 0.3371 1.750 0.6838 0.00880 0.00231 -0.0967 0.4112 0.3496 2.000 0.7037 0.00907 0.00247 -0.0952 0.3833 0.3638 2.250 0.7245 0.00928 0.00262 -0.0938 0.3626 0.3800 2.500 0.7460 0.00945 0.00276 -0.0925 0.3479 0.3978 2.750 0.7673 0.00961 0.00290 -0.0912 0.3355 0.4147 3.000 0.7892 0.00974 0.00303 -0.0900 0.3253 0.4323 3.250 0.8101 0.00988 0.00317 -0.0886 0.3159 0.4524 3.500 0.8298 0.00999 0.00330 -0.0869 0.3073 0.4731 3.750 0.8482 0.01010 0.00343 -0.0850 0.2991 0.4962 4.000 0.8672 0.01018 0.00357 -0.0833 0.2920 0.5315 4.250 0.8815 0.01014 0.00378 -0.0806 0.2847 0.6363 4.750 1.0117 0.01015 0.00448 -0.0971 0.2701 1.0000 5.000 1.0290 0.01032 0.00462 -0.0950 0.2655 1.0000 5.250 1.0474 0.01047 0.00477 -0.0931 0.2614 1.0000 5.500 1.0656 0.01066 0.00493 -0.0912 0.2571 1.0000 5.750 1.0833 0.01088 0.00512 -0.0893 0.2524 1.0000 6.000 1.1026 0.01108 0.00531 -0.0877 0.2488 1.0000 6.250 1.1224 0.01127 0.00550 -0.0862 0.2450 1.0000 6.500 1.1417 0.01151 0.00571 -0.0847 0.2404 1.0000 6.750 1.1600 0.01179 0.00597 -0.0831 0.2354 1.0000 7.000 1.1800 0.01203 0.00621 -0.0817 0.2317 1.0000 7.250 1.1997 0.01229 0.00646 -0.0804 0.2273 1.0000 7.500 1.2183 0.01260 0.00675 -0.0789 0.2220 1.0000 7.750 1.2369 0.01293 0.00706 -0.0775 0.2171 1.0000 8.000 1.2560 0.01325 0.00737 -0.0762 0.2119 1.0000 8.250 1.2736 0.01365 0.00774 -0.0747 0.2056 1.0000 8.500 1.2918 0.01404 0.00811 -0.0734 0.2001 1.0000 8.750 1.3096 0.01445 0.00851 -0.0720 0.1939 1.0000 9.000 1.3262 0.01494 0.00897 -0.0705 0.1878 1.0000 9.250 1.3440 0.01538 0.00940 -0.0692 0.1825 1.0000 9.500 1.3601 0.01592 0.00992 -0.0677 0.1763 1.0000 9.750 1.3764 0.01645 0.01044 -0.0663 0.1708 1.0000 10.000 1.3910 0.01710 0.01106 -0.0647 0.1629 1.0000 10.250 1.4055 0.01778 0.01171 -0.0632 0.1557 1.0000 10.500 1.4189 0.01853 0.01242 -0.0616 0.1483 1.0000 10.750 1.4330 0.01926 0.01314 -0.0602 0.1420 1.0000 11.000 1.4478 0.01997 0.01385 -0.0589 0.1377 1.0000 11.250 1.4614 0.02078 0.01465 -0.0575 0.1336 1.0000 11.500 1.4765 0.02150 0.01539 -0.0563 0.1302 1.0000 11.750 1.4907 0.02230 0.01620 -0.0551 0.1269 1.0000 12.000 1.5031 0.02323 0.01712 -0.0538 0.1227 1.0000 12.250 1.5159 0.02416 0.01807 -0.0526 0.1192 1.0000 12.500 1.5301 0.02501 0.01894 -0.0516 0.1170 1.0000 12.750 1.5420 0.02604 0.01998 -0.0504 0.1136 1.0000 13.000 1.5539 0.02710 0.02105 -0.0493 0.1110 1.0000 13.250 1.5652 0.02823 0.02220 -0.0482 0.1080 1.0000 13.500 1.5780 0.02926 0.02327 -0.0473 0.1061 1.0000 13.750 1.5899 0.03037 0.02442 -0.0463 0.1037 1.0000 14.000 1.5999 0.03167 0.02573 -0.0453 0.1010 1.0000 14.250 1.6088 0.03307 0.02714 -0.0443 0.0979 1.0000 14.500 1.6194 0.03436 0.02848 -0.0435 0.0960 1.0000 14.750 1.6293 0.03572 0.02987 -0.0426 0.0926 1.0000 15.000 1.6338 0.03755 0.03168 -0.0416 0.0870 1.0000 15.250 1.6425 0.03907 0.03324 -0.0408 0.0848 1.0000 15.500 1.6490 0.04080 0.03498 -0.0400 0.0800 1.0000 15.750 1.6476 0.04327 0.03742 -0.0389 0.0708 1.0000 16.250 1.6084 0.05206 0.04603 -0.0362 0.0382 1.0000 16.500 1.5874 0.05692 0.05087 -0.0353 0.0257 1.0000 16.750 1.5743 0.06112 0.05509 -0.0348 0.0191 1.0000 17.000 1.5694 0.06451 0.05854 -0.0346 0.0170 1.0000 17.250 1.5656 0.06782 0.06191 -0.0345 0.0156 1.0000 17.500 1.5615 0.07124 0.06540 -0.0346 0.0146 1.0000 17.750 1.5571 0.07476 0.06899 -0.0348 0.0137 1.0000 18.000 1.5532 0.07830 0.07261 -0.0351 0.0133 1.0000 18.250 1.5469 0.08216 0.07655 -0.0355 0.0129 1.0000 18.500 1.5396 0.08625 0.08072 -0.0360 0.0125 1.0000 18.750 1.5317 0.09047 0.08504 -0.0367 0.0122 1.0000 19.000 1.5245 0.09468 0.08934 -0.0375 0.0119 1.0000 19.250 1.5163 0.09904 0.09379 -0.0385 0.0117 1.0000