XFOIL Version 6.94 Calculated polar for: NACA 63(3)-618 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 0.4814 0.01257 0.00644 -0.1067 0.6382 0.6207 0.500 0.5375 0.01269 0.00657 -0.1068 0.6293 0.6317 1.000 0.5947 0.01279 0.00664 -0.1072 0.6204 0.6419 1.500 0.6529 0.01307 0.00682 -0.1079 0.6078 0.6483 2.000 0.7075 0.01327 0.00709 -0.1082 0.5987 0.6623 2.500 0.7603 0.01339 0.00733 -0.1078 0.5928 0.6733 3.000 0.8139 0.01349 0.00748 -0.1075 0.5836 0.6847 3.500 0.8690 0.01364 0.00764 -0.1076 0.5745 0.6946 4.000 0.9241 0.01376 0.00776 -0.1078 0.5656 0.7064 4.500 0.9766 0.01452 0.00857 -0.1075 0.5503 0.7203 5.000 1.0246 0.01459 0.00880 -0.1061 0.5453 0.7344 5.500 1.0733 0.01464 0.00895 -0.1049 0.5352 0.7456 6.000 1.1216 0.01446 0.00899 -0.1036 0.5214 0.7606 6.500 1.1681 0.01461 0.00911 -0.1017 0.4984 0.7752 7.000 1.1959 0.01440 0.00904 -0.0964 0.4792 0.7905 7.500 1.2138 0.01459 0.00908 -0.0895 0.4491 0.8077 8.000 1.2232 0.01484 0.00958 -0.0811 0.4347 0.8304 9.000 1.2308 0.01621 0.01107 -0.0642 0.3902 0.8838 9.500 1.2150 0.01721 0.01215 -0.0533 0.3603 0.9418 10.000 1.2239 0.01922 0.01404 -0.0494 0.3201 1.0000 10.500 1.2194 0.02200 0.01665 -0.0440 0.2816 1.0000 11.000 1.2047 0.02555 0.02002 -0.0382 0.2422 1.0000 11.500 1.1939 0.02931 0.02364 -0.0336 0.2077 1.0000 12.000 1.1926 0.03290 0.02717 -0.0303 0.1776 1.0000 12.500 1.1789 0.03775 0.03190 -0.0270 0.1483 1.0000 13.000 1.1861 0.04134 0.03551 -0.0251 0.1281 1.0000 13.500 1.1751 0.04672 0.04080 -0.0233 0.1042 1.0000 14.000 1.1745 0.05150 0.04555 -0.0223 0.0823 1.0000 14.500 1.1640 0.05770 0.05165 -0.0217 0.0661 1.0000 15.000 1.1581 0.06385 0.05774 -0.0218 0.0522 1.0000 15.500 1.1582 0.06967 0.06367 -0.0222 0.0419 1.0000 16.000 1.1633 0.07511 0.06932 -0.0230 0.0356 1.0000 16.500 1.1512 0.08308 0.07737 -0.0247 0.0288 1.0000 17.000 1.1398 0.09117 0.08574 -0.0259 0.0226 1.0000 17.500 1.1386 0.09803 0.09304 -0.0266 0.0205 1.0000 18.000 1.1384 0.10536 0.10067 -0.0287 0.0201 1.0000 18.500 1.1307 0.11400 0.10961 -0.0322 0.0199 1.0000 19.000 1.1250 0.12240 0.11826 -0.0360 0.0198 1.0000 19.500 1.1082 0.13301 0.12916 -0.0414 0.0196 1.0000 20.000 1.0864 0.14473 0.14117 -0.0476 0.0195 1.0000