XFOIL Version 6.94 Calculated polar for: EPPLER 377 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 0.6347 0.02571 0.02036 -0.1159 0.5765 0.0450 0.500 0.7034 0.02291 0.01719 -0.1189 0.5664 0.0502 1.000 0.7700 0.02025 0.01429 -0.1210 0.5565 0.0566 1.500 0.8488 0.01296 0.00541 -0.1237 0.5483 0.0375 2.000 0.9044 0.01239 0.00471 -0.1231 0.5383 0.0557 2.500 0.9585 0.01292 0.00525 -0.1226 0.5288 0.0941 3.000 1.0127 0.01287 0.00519 -0.1221 0.5190 0.1097 3.500 1.0666 0.01278 0.00511 -0.1215 0.5094 0.1284 4.000 1.1202 0.01289 0.00529 -0.1209 0.4993 0.1562 4.500 1.1735 0.01296 0.00542 -0.1203 0.4883 0.1929 5.000 1.2265 0.01307 0.00571 -0.1197 0.4762 0.2413 5.500 1.2793 0.01317 0.00604 -0.1191 0.4644 0.3487 7.000 1.4349 0.01297 0.00638 -0.1170 0.3697 1.0000 7.500 1.4832 0.01366 0.00701 -0.1160 0.3270 1.0000 8.000 1.5197 0.01590 0.00859 -0.1141 0.2064 1.0000 8.500 1.5503 0.01881 0.01092 -0.1117 0.1091 1.0000 9.000 1.5752 0.02191 0.01358 -0.1085 0.0403 1.0000 9.500 1.5865 0.02561 0.01714 -0.1036 0.0036 1.0000 10.000 1.5985 0.02812 0.01993 -0.0984 0.0031 1.0000 10.500 1.5952 0.03158 0.02369 -0.0928 0.0029 1.0000 11.000 1.5898 0.03659 0.02902 -0.0899 0.0028 1.0000 11.500 1.5819 0.04278 0.03553 -0.0884 0.0028 1.0000 12.000 1.5702 0.05008 0.04314 -0.0879 0.0028 1.0000 12.500 1.5558 0.05825 0.05158 -0.0882 0.0028 1.0000 13.000 1.5413 0.06693 0.06052 -0.0892 0.0028 1.0000 13.500 1.5285 0.07592 0.06976 -0.0907 0.0029 1.0000 14.000 1.5193 0.08497 0.07904 -0.0925 0.0029 1.0000 14.500 1.5137 0.09375 0.08809 -0.0942 0.0030 1.0000 15.000 1.5120 0.10202 0.09664 -0.0953 0.0032 1.0000 15.500 1.5085 0.11118 0.10619 -0.0971 0.0035 1.0000 16.000 1.4997 0.12187 0.11729 -0.1007 0.0037 1.0000 16.500 1.4869 0.13380 0.12960 -0.1060 0.0039 1.0000 17.000 1.4722 0.14649 0.14264 -0.1127 0.0040 1.0000 17.500 1.4615 0.15846 0.15488 -0.1193 0.0042 1.0000 18.000 1.4421 0.17425 0.17109 -0.1302 0.0044 1.0000 18.500 1.4161 0.19345 0.19070 -0.1435 0.0045 1.0000 19.000 1.3945 0.21307 0.21060 -0.1570 0.0046 1.0000 20.000 1.3620 0.25882 0.25647 -0.1831 0.0060 1.0000 20.500 1.1273 0.31713 0.31534 -0.1899 0.0170 1.0000 21.000 1.1315 0.32940 0.32762 -0.1938 0.0165 1.0000 21.500 1.1328 0.34361 0.34184 -0.1986 0.0148 1.0000 22.000 1.1419 0.35244 0.35072 -0.2002 0.0141 1.0000 22.500 1.1404 0.36921 0.36748 -0.2062 0.0130 1.0000 23.000 1.1454 0.38026 0.37856 -0.2093 0.0120 1.0000 23.500 1.1489 0.39347 0.39178 -0.2128 0.0116 1.0000 24.000 1.1524 0.40699 0.40533 -0.2167 0.0105 1.0000 24.500 1.1565 0.41859 0.41697 -0.2197 0.0098 1.0000 25.000 1.1599 0.43191 0.43030 -0.2228 0.0095 1.0000 25.500 1.1628 0.44575 0.44416 -0.2265 0.0088 1.0000 26.000 1.1659 0.45850 0.45695 -0.2296 0.0080 1.0000 26.500 1.1688 0.47027 0.46876 -0.2322 0.0077 1.0000 27.000 1.1711 0.48423 0.48274 -0.2356 0.0075 1.0000 27.500 1.1736 0.49895 0.49748 -0.2390 0.0070 1.0000 28.000 1.1756 0.51241 0.51097 -0.2418 0.0065 1.0000 28.500 1.1772 0.52516 0.52376 -0.2448 0.0061 1.0000 29.000 1.1785 0.53738 0.53603 -0.2474 0.0059 1.0000 29.500 1.1792 0.55127 0.54994 -0.2501 0.0058 1.0000 30.000 1.1799 0.56550 0.56421 -0.2532 0.0057 1.0000 30.500 1.1807 0.57953 0.57828 -0.2562 0.0055 1.0000 31.000 1.1810 0.59353 0.59231 -0.2589 0.0052 1.0000 31.500 1.1810 0.60713 0.60595 -0.2616 0.0049 1.0000 32.000 1.1803 0.62060 0.61945 -0.2641 0.0047 1.0000 32.500 1.1793 0.63435 0.63324 -0.2666 0.0045 1.0000 33.000 1.1772 0.64637 0.64531 -0.2690 0.0042 1.0000 33.500 1.1762 0.66157 0.66052 -0.2717 0.0041 1.0000 34.000 1.1756 0.67748 0.67646 -0.2742 0.0034 1.0000 34.500 1.1732 0.69070 0.68972 -0.2765 0.0030 1.0000 35.000 1.1702 0.70389 0.70294 -0.2788 0.0029 1.0000 36.000 1.1650 0.73327 0.73237 -0.2834 0.0027 1.0000 36.500 1.1622 0.74681 0.74595 -0.2856 0.0026 1.0000 37.000 1.1588 0.76068 0.75984 -0.2878 0.0024 1.0000 37.500 1.1548 0.77384 0.77304 -0.2898 0.0022 1.0000 38.000 1.1506 0.78771 0.78694 -0.2918 0.0021 1.0000 38.500 1.1459 0.80002 0.79928 -0.2938 0.0019 1.0000 39.000 1.1406 0.81179 0.81109 -0.2959 0.0018 1.0000 39.500 1.1352 0.82419 0.82353 -0.2979 0.0017 1.0000 40.500 1.1238 0.84982 0.84920 -0.3016 0.0016 1.0000 41.000 1.1182 0.86213 0.86154 -0.3033 0.0016 1.0000 41.500 1.1129 0.87557 0.87501 -0.3050 0.0012 1.0000 42.000 1.1062 0.88690 0.88636 -0.3067 0.0011 1.0000 42.500 1.0992 0.89749 0.89699 -0.3084 0.0010 1.0000 43.000 1.0915 0.90762 0.90715 -0.3099 0.0009 1.0000 43.500 1.0834 0.91774 0.91730 -0.3115 0.0008 1.0000 45.000 1.0591 0.94779 0.94743 -0.3158 0.0008 1.0000 45.500 1.0513 0.95717 0.95684 -0.3173 0.0008 1.0000 46.000 1.0419 0.96389 0.96359 -0.3185 0.0008 1.0000 46.500 1.0338 0.97380 0.97352 -0.3197 0.0008 1.0000 47.000 1.0244 0.98096 0.98071 -0.3209 0.0008 1.0000 47.500 1.0145 0.98632 0.98610 -0.3220 0.0008 1.0000 48.000 1.0051 0.99391 0.99372 -0.3231 0.0007 1.0000 48.500 0.9946 0.99807 0.99791 -0.3242 0.0007 1.0000 49.000 0.9843 1.00350 1.00338 -0.3252 0.0007 1.0000 49.500 0.9740 1.00852 1.00842 -0.3262 0.0007 1.0000 50.000 0.9631 1.01214 1.01207 -0.3270 0.0006 1.0000 50.500 0.9523 1.01657 1.01653 -0.3280 0.0006 1.0000 51.000 0.9409 1.01934 1.01932 -0.3287 0.0006 1.0000 51.500 0.9296 1.02224 1.02224 -0.3295 0.0006 1.0000 52.000 0.9180 1.02363 1.02367 -0.3302 0.0005 1.0000 52.500 0.9061 1.02485 1.02491 -0.3309 0.0005 1.0000 53.000 0.8941 1.02526 1.02535 -0.3314 0.0004 1.0000 53.500 0.8820 1.02516 1.02527 -0.3320 0.0004 1.0000 54.000 0.8695 1.02484 1.02498 -0.3325 0.0003 1.0000 54.500 0.8569 1.02318 1.02334 -0.3330 0.0003 1.0000 55.000 0.8440 1.02145 1.02163 -0.3335 0.0003 1.0000 56.500 0.8056 1.01483 1.01506 -0.3343 0.0003 1.0000 57.000 0.7930 1.01132 1.01157 -0.3345 0.0003 1.0000 57.500 0.7799 1.00791 1.00818 -0.3345 0.0003 1.0000 58.000 0.7666 1.00237 1.00266 -0.3345 0.0002 1.0000 58.500 0.7531 0.99654 0.99685 -0.3346 0.0002 1.0000 59.000 0.7395 0.98950 0.98983 -0.3345 0.0002 1.0000 59.500 0.7258 0.98338 0.98372 -0.3344 0.0002 1.0000 60.000 0.7120 0.97565 0.97601 -0.3343 0.0002 1.0000