XFOIL Version 6.94 Calculated polar for: OAF102 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4742 0.01065 0.00423 -0.1203 0.7687 0.4874 0.500 0.5323 0.01066 0.00430 -0.1205 0.7550 0.5168 1.000 0.5913 0.01066 0.00445 -0.1210 0.7413 0.5497 1.500 0.6497 0.01069 0.00463 -0.1213 0.7284 0.5888 2.000 0.7079 0.01059 0.00485 -0.1216 0.7145 0.6548 3.000 0.8118 0.01002 0.00498 -0.1187 0.6792 1.0000 3.500 0.8678 0.00997 0.00481 -0.1181 0.6370 1.0000 4.000 0.9248 0.01015 0.00493 -0.1179 0.5996 1.0000 4.500 0.9808 0.01048 0.00515 -0.1176 0.5416 1.0000 5.000 1.0302 0.01200 0.00581 -0.1168 0.3583 1.0000 5.500 1.0663 0.01623 0.00830 -0.1154 0.0767 1.0000 6.000 1.1129 0.01805 0.00999 -0.1142 0.0547 1.0000 6.500 1.1584 0.01976 0.01172 -0.1126 0.0448 1.0000 7.500 1.2390 0.02401 0.01597 -0.1080 0.0340 1.0000 8.000 1.2787 0.02616 0.01816 -0.1057 0.0301 1.0000 9.500 1.4000 0.03520 0.02798 -0.0984 0.0238 1.0000 10.000 1.4360 0.03896 0.03194 -0.0961 0.0222 1.0000 10.500 1.4551 0.04463 0.03842 -0.0913 0.0214 1.0000 11.000 1.4546 0.05160 0.04613 -0.0848 0.0211 1.0000 11.500 1.4267 0.05907 0.05426 -0.0764 0.0213 1.0000 12.000 1.3893 0.06782 0.06356 -0.0710 0.0216 1.0000 12.500 1.3509 0.07763 0.07381 -0.0691 0.0219 1.0000 13.000 1.3148 0.08839 0.08489 -0.0701 0.0222 1.0000 13.500 1.2940 0.09874 0.09540 -0.0720 0.0225 1.0000 14.500 0.9338 0.13835 0.13603 -0.0789 0.0263 1.0000 16.000 0.8129 0.19465 0.19233 -0.1059 0.0356 1.0000 18.000 0.8278 0.22142 0.21914 -0.1140 0.0299 1.0000 18.500 0.8196 0.23023 0.22795 -0.1193 0.0273 1.0000 19.500 0.8262 0.24451 0.24225 -0.1243 0.0244 1.0000 20.000 0.8323 0.25067 0.24843 -0.1262 0.0230 1.0000 20.500 0.8383 0.25749 0.25527 -0.1279 0.0224 1.0000 21.000 0.8388 0.26586 0.26364 -0.1315 0.0206 1.0000 21.500 0.8454 0.27186 0.26967 -0.1332 0.0194 1.0000 22.000 0.8481 0.27988 0.27770 -0.1360 0.0187 1.0000 22.500 0.8522 0.28741 0.28524 -0.1386 0.0172 1.0000 23.000 0.8580 0.29368 0.29153 -0.1404 0.0163 1.0000 23.500 0.8618 0.30139 0.29925 -0.1428 0.0158 1.0000 24.000 0.8654 0.30940 0.30728 -0.1456 0.0146 1.0000 24.500 0.8700 0.31632 0.31422 -0.1478 0.0137 1.0000 25.000 0.8753 0.32268 0.32060 -0.1495 0.0132 1.0000 25.500 0.8785 0.33065 0.32858 -0.1520 0.0130 1.0000 26.000 0.8817 0.33889 0.33684 -0.1547 0.0124 1.0000 26.500 0.8855 0.34630 0.34427 -0.1570 0.0116 1.0000 27.000 0.8892 0.35337 0.35137 -0.1592 0.0110 1.0000 27.500 0.8930 0.35981 0.35784 -0.1610 0.0106 1.0000 28.000 0.8954 0.36827 0.36631 -0.1637 0.0103 1.0000 28.500 0.8984 0.37634 0.37440 -0.1661 0.0095 1.0000 29.000 0.9012 0.38373 0.38182 -0.1683 0.0088 1.0000 29.500 0.9037 0.39069 0.38880 -0.1705 0.0083 1.0000 30.500 0.9077 0.40565 0.40381 -0.1747 0.0080 1.0000 31.000 0.9096 0.41375 0.41193 -0.1772 0.0078 1.0000 31.500 0.9114 0.42144 0.41964 -0.1794 0.0074 1.0000 32.000 0.9128 0.42882 0.42705 -0.1816 0.0070 1.0000 32.500 0.9139 0.43604 0.43430 -0.1838 0.0066 1.0000 33.000 0.9147 0.44290 0.44119 -0.1860 0.0062 1.0000 33.500 0.9149 0.44932 0.44764 -0.1880 0.0059 1.0000 34.500 0.9153 0.46472 0.46309 -0.1925 0.0057 1.0000 35.000 0.9156 0.47233 0.47073 -0.1946 0.0055 1.0000 35.500 0.9154 0.47953 0.47796 -0.1967 0.0051 1.0000 36.000 0.9147 0.48642 0.48487 -0.1988 0.0048 1.0000 36.500 0.9137 0.49309 0.49157 -0.2009 0.0045 1.0000 37.000 0.9125 0.49955 0.49806 -0.2031 0.0043 1.0000 37.500 0.9108 0.50572 0.50426 -0.2052 0.0041 1.0000 38.000 0.9086 0.51166 0.51024 -0.2072 0.0040 1.0000 39.500 0.9021 0.53129 0.52995 -0.2134 0.0039 1.0000 40.000 0.8998 0.53767 0.53635 -0.2154 0.0038 1.0000 40.500 0.8971 0.54381 0.54252 -0.2173 0.0036 1.0000 41.000 0.8940 0.54968 0.54843 -0.2193 0.0034 1.0000 41.500 0.8906 0.55534 0.55411 -0.2212 0.0031 1.0000 42.000 0.8869 0.56068 0.55948 -0.2232 0.0029 1.0000 42.500 0.8830 0.56580 0.56463 -0.2251 0.0027 1.0000 43.000 0.8787 0.57057 0.56944 -0.2271 0.0026 1.0000 43.500 0.8741 0.57508 0.57397 -0.2290 0.0024 1.0000 44.000 0.8688 0.57927 0.57820 -0.2309 0.0023 1.0000 46.000 0.8486 0.59743 0.59647 -0.2382 0.0022 1.0000 46.500 0.8431 0.60149 0.60056 -0.2399 0.0022 1.0000 47.000 0.8374 0.60521 0.60431 -0.2416 0.0021 1.0000 47.500 0.8314 0.60866 0.60778 -0.2433 0.0020 1.0000 48.000 0.8251 0.61181 0.61097 -0.2449 0.0019 1.0000 48.500 0.8186 0.61469 0.61387 -0.2466 0.0017 1.0000 49.000 0.8118 0.61726 0.61647 -0.2483 0.0016 1.0000 49.500 0.8048 0.61955 0.61879 -0.2499 0.0014 1.0000 50.000 0.7976 0.62144 0.62071 -0.2516 0.0013 1.0000 50.500 0.7902 0.62307 0.62237 -0.2532 0.0012 1.0000 51.000 0.7823 0.62428 0.62361 -0.2549 0.0011 1.0000 53.000 0.7511 0.63011 0.62953 -0.2608 0.0010 1.0000 53.500 0.7429 0.63087 0.63032 -0.2621 0.0010 1.0000 54.000 0.7347 0.63135 0.63083 -0.2635 0.0010 1.0000 54.500 0.7262 0.63159 0.63109 -0.2649 0.0009 1.0000 55.000 0.7175 0.63145 0.63097 -0.2662 0.0009 1.0000 55.500 0.7087 0.63109 0.63064 -0.2675 0.0008 1.0000 56.000 0.6998 0.63044 0.63002 -0.2688 0.0007 1.0000 56.500 0.6907 0.62957 0.62917 -0.2700 0.0006 1.0000 57.000 0.6814 0.62842 0.62804 -0.2713 0.0006 1.0000 57.500 0.6720 0.62691 0.62655 -0.2725 0.0005 1.0000 58.000 0.6625 0.62510 0.62477 -0.2738 0.0004 1.0000 58.500 0.6528 0.62297 0.62266 -0.2750 0.0004 1.0000 59.000 0.6428 0.62041 0.62013 -0.2762 0.0003 1.0000