XFOIL Version 6.90 Calculated polar for: Eppler 387 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 11.000 alpha CL CD CDp CM Top Xtr Bot Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0560 0.02350 0.01498 -0.0988 0.9417 0.0994 -2.900 0.0725 0.02284 0.01431 -0.0997 0.9384 0.1034 -2.800 0.0920 0.02213 0.01360 -0.1013 0.9361 0.1128 -2.700 0.1121 0.02138 0.01290 -0.1029 0.9341 0.1252 -2.600 0.1330 0.02070 0.01217 -0.1045 0.9324 0.1443 -2.400 0.1588 0.01962 0.01143 -0.1054 0.9245 0.1926 -2.100 0.1963 0.01636 0.01058 -0.1056 0.9170 0.6517 -1.900 0.2190 0.01570 0.01026 -0.1033 0.9104 1.0000 -1.800 0.2368 0.01571 0.01006 -0.1045 0.9079 1.0000 -1.700 0.2458 0.01589 0.01010 -0.1043 0.9028 1.0000 -1.600 0.2595 0.01597 0.01003 -0.1048 0.8992 1.0000 -1.500 0.2750 0.01599 0.00990 -0.1055 0.8965 1.0000 -1.400 0.2863 0.01613 0.00992 -0.1057 0.8925 1.0000 -1.300 0.2970 0.01627 0.00996 -0.1057 0.8882 1.0000 -1.200 0.3107 0.01633 0.00990 -0.1061 0.8852 1.0000 -1.100 0.3251 0.01635 0.00982 -0.1065 0.8829 1.0000 -1.000 0.3331 0.01660 0.01000 -0.1063 0.8778 1.0000 -0.900 0.3449 0.01670 0.01001 -0.1064 0.8743 1.0000 -0.800 0.3581 0.01675 0.00997 -0.1066 0.8717 1.0000 -0.700 0.3688 0.01690 0.01005 -0.1066 0.8682 1.0000 -0.600 0.3785 0.01710 0.01017 -0.1066 0.8639 1.0000 -0.500 0.3905 0.01718 0.01018 -0.1066 0.8609 1.0000 -0.400 0.4031 0.01722 0.01015 -0.1066 0.8586 1.0000 -0.300 0.4123 0.01748 0.01035 -0.1066 0.8543 1.0000 -0.200 0.4227 0.01764 0.01047 -0.1066 0.8507 1.0000 -0.100 0.4345 0.01772 0.01048 -0.1065 0.8479 1.0000 0.000 0.4466 0.01777 0.01047 -0.1064 0.8458 1.0000 0.100 0.4554 0.01808 0.01075 -0.1065 0.8412 1.0000 0.200 0.4660 0.01824 0.01086 -0.1064 0.8378 1.0000 0.300 0.4775 0.01832 0.01089 -0.1063 0.8353 1.0000 0.400 0.4894 0.01837 0.01089 -0.1062 0.8333 1.0000 0.500 0.4982 0.01873 0.01123 -0.1063 0.8286 1.0000 0.600 0.5087 0.01890 0.01136 -0.1063 0.8254 1.0000 0.700 0.5201 0.01898 0.01140 -0.1061 0.8229 1.0000 0.800 0.5316 0.01903 0.01141 -0.1059 0.8209 1.0000 0.900 0.5406 0.01942 0.01179 -0.1061 0.8164 1.0000 1.000 0.5510 0.01961 0.01196 -0.1061 0.8132 1.0000 1.100 0.5622 0.01970 0.01202 -0.1059 0.8107 1.0000 1.200 0.5736 0.01976 0.01204 -0.1056 0.8087 1.0000 1.300 0.5828 0.02015 0.01243 -0.1059 0.8045 1.0000 1.400 0.5930 0.02037 0.01264 -0.1059 0.8011 1.0000 1.500 0.6041 0.02048 0.01273 -0.1057 0.7986 1.0000 1.600 0.6154 0.02054 0.01276 -0.1054 0.7966 1.0000 1.700 0.6248 0.02092 0.01314 -0.1056 0.7928 1.0000 1.800 0.6348 0.02119 0.01341 -0.1057 0.7893 1.0000 1.900 0.6457 0.02131 0.01354 -0.1055 0.7867 1.0000 2.000 0.6570 0.02137 0.01357 -0.1052 0.7846 1.0000 2.100 0.6667 0.02171 0.01391 -0.1053 0.7812 1.0000 2.200 0.6763 0.02204 0.01426 -0.1054 0.7774 1.0000 2.300 0.6871 0.02218 0.01439 -0.1052 0.7746 1.0000 2.400 0.6983 0.02223 0.01443 -0.1049 0.7725 1.0000 2.500 0.7083 0.02250 0.01471 -0.1049 0.7695 1.0000 2.600 0.7175 0.02292 0.01515 -0.1051 0.7653 1.0000 2.700 0.7282 0.02305 0.01529 -0.1049 0.7625 1.0000 2.800 0.7394 0.02309 0.01531 -0.1045 0.7603 1.0000 2.900 0.7494 0.02335 0.01562 -0.1044 0.7572 1.0000 3.000 0.7584 0.02378 0.01609 -0.1046 0.7528 1.0000 3.100 0.7691 0.02389 0.01620 -0.1043 0.7499 1.0000 3.200 0.7804 0.02389 0.01619 -0.1038 0.7476 1.0000 3.300 0.7896 0.02428 0.01661 -0.1039 0.7437 1.0000 3.400 0.7990 0.02461 0.01697 -0.1039 0.7396 1.0000 3.500 0.8099 0.02464 0.01701 -0.1034 0.7368 1.0000 3.600 0.8213 0.02456 0.01692 -0.1028 0.7346 1.0000 3.700 0.8292 0.02516 0.01758 -0.1031 0.7292 1.0000 3.800 0.8396 0.02523 0.01767 -0.1027 0.7255 1.0000 3.900 0.8510 0.02505 0.01752 -0.1019 0.7228 1.0000 4.000 0.8591 0.02546 0.01799 -0.1018 0.7172 1.0000 4.100 0.8695 0.02542 0.01796 -0.1012 0.7129 1.0000 4.200 0.8810 0.02512 0.01764 -0.1002 0.7100 1.0000 4.300 0.8887 0.02559 0.01818 -0.1002 0.7036 1.0000 4.400 0.8995 0.02546 0.01806 -0.0994 0.6998 1.0000 4.500 0.9112 0.02517 0.01775 -0.0985 0.6972 1.0000 4.600 0.9187 0.02575 0.01842 -0.0987 0.6906 1.0000 4.700 0.9296 0.02564 0.01834 -0.0980 0.6871 1.0000 4.800 0.9414 0.02542 0.01811 -0.0973 0.6848 1.0000 5.000 0.9598 0.02594 0.01875 -0.0969 0.6748 1.0000 5.100 0.9717 0.02568 0.01853 -0.0961 0.6724 1.0000 5.300 0.9903 0.02610 0.01908 -0.0955 0.6620 1.0000 5.400 0.9998 0.02619 0.01923 -0.0950 0.6569 1.0000 5.500 1.0096 0.02612 0.01921 -0.0943 0.6511 1.0000 5.600 1.0221 0.02551 0.01855 -0.0931 0.6476 1.0000 5.700 1.0295 0.02575 0.01891 -0.0927 0.6392 1.0000 5.800 1.0413 0.02518 0.01830 -0.0915 0.6343 1.0000 5.900 1.0499 0.02511 0.01832 -0.0908 0.6261 1.0000 6.000 1.0598 0.02484 0.01808 -0.0899 0.6194 1.0000 6.100 1.0705 0.02445 0.01769 -0.0890 0.6128 1.0000 6.200 1.0796 0.02434 0.01765 -0.0883 0.6050 1.0000 6.300 1.0913 0.02379 0.01712 -0.0873 0.5992 1.0000 6.400 1.0999 0.02374 0.01718 -0.0866 0.5905 1.0000 6.500 1.1110 0.02333 0.01676 -0.0858 0.5843 1.0000 6.600 1.1205 0.02315 0.01665 -0.0851 0.5761 1.0000 6.700 1.1298 0.02301 0.01659 -0.0844 0.5678 1.0000 6.800 1.1417 0.02253 0.01609 -0.0836 0.5615 1.0000 6.900 1.1502 0.02244 0.01612 -0.0829 0.5516 1.0000 7.000 1.1595 0.02224 0.01601 -0.0822 0.5420 1.0000 7.100 1.1693 0.02193 0.01575 -0.0814 0.5321 1.0000 7.200 1.1789 0.02159 0.01545 -0.0805 0.5213 1.0000 7.300 1.1880 0.02127 0.01521 -0.0796 0.5087 1.0000 7.400 1.1965 0.02097 0.01499 -0.0787 0.4940 1.0000 7.500 1.2050 0.02057 0.01461 -0.0777 0.4767 1.0000 7.600 1.2118 0.02025 0.01440 -0.0765 0.4529 1.0000 7.700 1.2175 0.02003 0.01418 -0.0752 0.4195 1.0000 7.800 1.2217 0.02007 0.01403 -0.0738 0.3744 1.0000 7.900 1.2234 0.02059 0.01418 -0.0724 0.3208 1.0000 8.000 1.2233 0.02152 0.01468 -0.0710 0.2748 1.0000 8.100 1.2227 0.02261 0.01542 -0.0696 0.2392 1.0000 8.200 1.2222 0.02371 0.01625 -0.0683 0.2104 1.0000 8.300 1.2217 0.02480 0.01712 -0.0670 0.1860 1.0000 8.400 1.2208 0.02592 0.01804 -0.0657 0.1637 1.0000 8.500 1.2186 0.02714 0.01906 -0.0641 0.1423 1.0000 9.000 1.2117 0.03330 0.02451 -0.0564 0.0811 1.0000