XFOIL Version 6.90 Calculated polar for: Eppler 387 1 elements 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) element 1 Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top Xtr Bot Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.1048 0.01946 0.01072 -0.1011 0.9086 0.0922 -2.900 0.1145 0.01905 0.01039 -0.1009 0.9029 0.0999 -2.800 0.1271 0.01856 0.00992 -0.1010 0.8993 0.1103 -2.700 0.1402 0.01812 0.00956 -0.1013 0.8964 0.1268 -2.600 0.1505 0.01776 0.00923 -0.1010 0.8914 0.1446 -2.500 0.1617 0.01730 0.00895 -0.1011 0.8875 0.1717 -2.400 0.1736 0.01670 0.00860 -0.1011 0.8845 0.2145 -2.300 0.1837 0.01611 0.00840 -0.1011 0.8804 0.2881 -2.200 0.1924 0.01544 0.00832 -0.1008 0.8761 0.4082 -2.100 0.2001 0.01482 0.00828 -0.0998 0.8729 0.5607 -2.000 0.2043 0.01437 0.00830 -0.0974 0.8701 0.7026 -1.900 0.2064 0.01411 0.00836 -0.0945 0.8652 0.8362 -1.800 0.2267 0.01386 0.00804 -0.0956 0.8620 1.0000 -1.700 0.2383 0.01389 0.00790 -0.0955 0.8590 1.0000 -1.600 0.2490 0.01398 0.00786 -0.0955 0.8547 1.0000 -1.500 0.2599 0.01406 0.00781 -0.0955 0.8505 1.0000 -1.400 0.2710 0.01411 0.00773 -0.0953 0.8474 1.0000 -1.200 0.2926 0.01429 0.00768 -0.0953 0.8397 1.0000 -1.000 0.3145 0.01440 0.00757 -0.0949 0.8337 1.0000 -0.800 0.3359 0.01461 0.00763 -0.0949 0.8258 1.0000 -0.600 0.3576 0.01473 0.00755 -0.0945 0.8204 1.0000 -0.400 0.3791 0.01498 0.00767 -0.0946 0.8125 1.0000 -0.200 0.4008 0.01510 0.00763 -0.0942 0.8075 1.0000 0.000 0.4222 0.01538 0.00782 -0.0943 0.7998 1.0000 0.200 0.4439 0.01551 0.00781 -0.0939 0.7950 1.0000 0.400 0.4654 0.01581 0.00804 -0.0941 0.7874 1.0000 0.600 0.4871 0.01596 0.00806 -0.0937 0.7827 1.0000 0.800 0.5086 0.01628 0.00835 -0.0939 0.7755 1.0000 1.000 0.5304 0.01644 0.00841 -0.0935 0.7706 1.0000 1.200 0.5518 0.01678 0.00872 -0.0937 0.7638 1.0000 1.400 0.5736 0.01697 0.00884 -0.0934 0.7588 1.0000 1.600 0.5950 0.01730 0.00916 -0.0935 0.7525 1.0000 1.800 0.6167 0.01754 0.00936 -0.0933 0.7471 1.0000 2.000 0.6382 0.01784 0.00964 -0.0933 0.7416 1.0000 2.200 0.6596 0.01813 0.00992 -0.0932 0.7355 1.0000 2.400 0.6814 0.01834 0.01009 -0.0929 0.7311 1.0000 2.600 0.7025 0.01875 0.01057 -0.0931 0.7240 1.0000 2.800 0.7244 0.01891 0.01069 -0.0927 0.7198 1.0000 3.000 0.7451 0.01938 0.01122 -0.0929 0.7124 1.0000 3.200 0.7669 0.01953 0.01136 -0.0924 0.7077 1.0000 3.400 0.7875 0.01998 0.01191 -0.0925 0.7003 1.0000 3.600 0.8092 0.02011 0.01203 -0.0920 0.6953 1.0000 3.800 0.8295 0.02053 0.01253 -0.0920 0.6875 1.0000 4.000 0.8514 0.02053 0.01252 -0.0913 0.6820 1.0000 4.100 0.8607 0.02079 0.01286 -0.0912 0.6764 1.0000 4.200 0.8712 0.02078 0.01286 -0.0908 0.6724 1.0000 4.300 0.8823 0.02067 0.01275 -0.0903 0.6695 1.0000 4.400 0.8916 0.02091 0.01307 -0.0902 0.6636 1.0000 4.500 0.9021 0.02088 0.01305 -0.0898 0.6596 1.0000 4.600 0.9133 0.02079 0.01293 -0.0893 0.6568 1.0000 4.700 0.9226 0.02106 0.01330 -0.0893 0.6512 1.0000 4.800 0.9332 0.02110 0.01337 -0.0890 0.6475 1.0000 4.900 0.9444 0.02106 0.01333 -0.0886 0.6448 1.0000 5.000 0.9540 0.02130 0.01366 -0.0885 0.6400 1.0000 5.100 0.9643 0.02140 0.01381 -0.0883 0.6358 1.0000 5.200 0.9754 0.02136 0.01378 -0.0880 0.6328 1.0000 5.300 0.9854 0.02152 0.01400 -0.0878 0.6284 1.0000 5.400 0.9954 0.02162 0.01420 -0.0875 0.6234 1.0000 5.500 1.0066 0.02145 0.01402 -0.0870 0.6197 1.0000 5.600 1.0157 0.02157 0.01424 -0.0867 0.6130 1.0000 5.700 1.0266 0.02137 0.01403 -0.0861 0.6079 1.0000 5.800 1.0360 0.02136 0.01410 -0.0856 0.6009 1.0000 5.900 1.0468 0.02109 0.01382 -0.0849 0.5951 1.0000 6.000 1.0560 0.02107 0.01389 -0.0844 0.5873 1.0000 6.100 1.0671 0.02078 0.01357 -0.0838 0.5817 1.0000 6.200 1.0760 0.02080 0.01370 -0.0834 0.5735 1.0000 6.300 1.0870 0.02056 0.01344 -0.0828 0.5676 1.0000 6.400 1.0961 0.02053 0.01356 -0.0823 0.5593 1.0000 6.500 1.1060 0.02045 0.01353 -0.0818 0.5519 1.0000 6.600 1.1163 0.02029 0.01341 -0.0813 0.5450 1.0000 6.700 1.1255 0.02029 0.01352 -0.0808 0.5365 1.0000 6.800 1.1358 0.02015 0.01341 -0.0803 0.5292 1.0000 6.900 1.1453 0.02008 0.01342 -0.0798 0.5203 1.0000 7.000 1.1544 0.02003 0.01348 -0.0793 0.5104 1.0000 7.100 1.1637 0.01995 0.01348 -0.0787 0.4999 1.0000 7.200 1.1728 0.01985 0.01346 -0.0781 0.4882 1.0000 7.300 1.1816 0.01977 0.01346 -0.0775 0.4749 1.0000 7.400 1.1903 0.01971 0.01347 -0.0768 0.4599 1.0000 7.500 1.1984 0.01965 0.01346 -0.0761 0.4411 1.0000 7.600 1.2055 0.01965 0.01347 -0.0753 0.4143 1.0000 7.700 1.2113 0.01978 0.01352 -0.0743 0.3772 1.0000 7.800 1.2151 0.02018 0.01362 -0.0731 0.3296 1.0000 7.900 1.2166 0.02093 0.01397 -0.0719 0.2827 1.0000 8.000 1.2176 0.02184 0.01455 -0.0708 0.2438 1.0000 8.100 1.2191 0.02276 0.01522 -0.0698 0.2131 1.0000 8.200 1.2206 0.02367 0.01595 -0.0688 0.1885 1.0000 8.300 1.2220 0.02459 0.01671 -0.0678 0.1669 1.0000 8.400 1.2224 0.02557 0.01750 -0.0667 0.1477 1.0000 8.500 1.2228 0.02655 0.01835 -0.0655 0.1267 1.0000 8.600 1.2212 0.02767 0.01929 -0.0642 0.1086 1.0000