XFOIL Version 6.96 Calculated polar for: GOE 703 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.7698 0.07321 0.06794 -0.0867 1.0000 0.0593 -15.250 -0.8000 0.06785 0.06240 -0.0874 1.0000 0.0591 -15.000 -0.8229 0.06358 0.05799 -0.0869 1.0000 0.0590 -14.750 -0.8469 0.05980 0.05403 -0.0856 1.0000 0.0588 -14.500 -0.8706 0.05646 0.05051 -0.0834 1.0000 0.0588 -14.250 -0.8911 0.05357 0.04743 -0.0805 1.0000 0.0587 -14.000 -0.9101 0.05109 0.04477 -0.0769 1.0000 0.0587 -13.750 -0.9269 0.04889 0.04239 -0.0730 1.0000 0.0587 -13.500 -0.9401 0.04698 0.04031 -0.0688 1.0000 0.0587 -13.250 -0.9555 0.04536 0.03852 -0.0639 1.0000 0.0588 -13.000 -0.9711 0.04398 0.03698 -0.0584 1.0000 0.0589 -12.750 -0.9884 0.04296 0.03582 -0.0523 1.0000 0.0590 -12.500 -1.0079 0.04221 0.03496 -0.0455 1.0000 0.0591 -12.250 -1.0294 0.04169 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0.01386 -0.0791 0.5779 0.9269 2.250 0.7578 0.02116 0.01399 -0.0774 0.5724 0.9351 2.500 0.7973 0.02095 0.01378 -0.0799 0.5661 0.9384 2.750 0.8277 0.02084 0.01370 -0.0807 0.5587 0.9438 3.000 0.8477 0.02101 0.01382 -0.0793 0.5529 0.9512 3.250 0.8857 0.02070 0.01350 -0.0816 0.5454 0.9549 3.500 0.9146 0.02056 0.01337 -0.0821 0.5375 0.9603 3.750 0.9404 0.02060 0.01333 -0.0819 0.5310 0.9667 4.000 0.9741 0.02025 0.01304 -0.0834 0.5223 0.9713 4.250 1.0020 0.02013 0.01289 -0.0837 0.5145 0.9769 4.500 1.0353 0.01989 0.01264 -0.0851 0.5068 0.9826 4.750 1.0671 0.01955 0.01232 -0.0862 0.4974 0.9881 5.000 1.1077 0.01914 0.01185 -0.0891 0.4891 0.9953 5.250 1.1404 0.01878 0.01156 -0.0906 0.4801 1.0000 5.500 1.1584 0.01885 0.01156 -0.0890 0.4739 1.0000 5.750 1.1723 0.01899 0.01178 -0.0866 0.4666 1.0000 6.000 1.1870 0.01909 0.01190 -0.0844 0.4595 1.0000 6.250 1.2051 0.01922 0.01195 -0.0828 0.4533 1.0000 6.500 1.2163 0.01939 0.01224 -0.0800 0.4455 1.0000 6.750 1.2309 0.01951 0.01234 -0.0777 0.4386 1.0000 7.000 1.2443 0.01970 0.01255 -0.0752 0.4313 1.0000 7.250 1.2547 0.01985 0.01274 -0.0722 0.4230 1.0000 7.500 1.2678 0.02004 0.01287 -0.0697 0.4155 1.0000 7.750 1.2750 0.02024 0.01316 -0.0660 0.4066 1.0000 8.000 1.2865 0.02045 0.01327 -0.0632 0.3989 1.0000 8.250 1.2903 0.02069 0.01363 -0.0590 0.3900 1.0000 8.500 1.2979 0.02094 0.01382 -0.0555 0.3822 1.0000 8.750 1.3004 0.02123 0.01419 -0.0511 0.3743 1.0000 9.000 1.3020 0.02151 0.01446 -0.0465 0.3664 1.0000 9.250 1.2974 0.02180 0.01477 -0.0408 0.3591 1.0000 9.500 1.2904 0.02209 0.01509 -0.0347 0.3516 1.0000 9.750 1.2852 0.02246 0.01542 -0.0291 0.3439 1.0000 10.000 1.2776 0.02287 0.01591 -0.0233 0.3357 1.0000 10.250 1.2739 0.02337 0.01633 -0.0183 0.3281 1.0000 10.500 1.2660 0.02394 0.01700 -0.0128 0.3193 1.0000 11.000 1.2527 0.02535 0.01843 -0.0029 0.3017 1.0000 11.250 1.2457 0.02621 0.01922 0.0018 0.2931 1.0000 11.500 1.2377 0.02716 0.02023 0.0064 0.2831 1.0000 11.750 1.2302 0.02823 0.02127 0.0107 0.2739 1.0000 12.000 1.2223 0.02940 0.02244 0.0148 0.2642 1.0000 12.250 1.2150 0.03066 0.02370 0.0186 0.2547 1.0000 12.500 1.2073 0.03204 0.02502 0.0222 0.2458 1.0000 12.750 1.2017 0.03343 0.02644 0.0254 0.2369 1.0000 13.000 1.1960 0.03490 0.02783 0.0285 0.2296 1.0000 13.250 1.1937 0.03630 0.02928 0.0311 0.2225 1.0000 13.500 1.1905 0.03780 0.03075 0.0336 0.2162 1.0000 13.750 1.1894 0.03925 0.03218 0.0359 0.2105 1.0000 14.000 1.1883 0.04079 0.03376 0.0379 0.2046 1.0000 14.250 1.1877 0.04229 0.03519 0.0399 0.1994 1.0000 14.500 1.1886 0.04381 0.03676 0.0416 0.1945 1.0000 14.750 1.1891 0.04543 0.03842 0.0432 0.1898 1.0000 15.000 1.1911 0.04690 0.03984 0.0447 0.1853 1.0000 15.250 1.1937 0.04842 0.04139 0.0461 0.1811 1.0000 15.500 1.1941 0.05021 0.04326 0.0473 0.1769 1.0000 15.750 1.1955 0.05192 0.04496 0.0485 0.1726 1.0000 16.000 1.2010 0.05325 0.04624 0.0497 0.1685 1.0000 16.250 1.1984 0.05550 0.04863 0.0506 0.1643 1.0000 16.500 1.1979 0.05756 0.05072 0.0514 0.1599 1.0000 16.750 1.2018 0.05911 0.05219 0.0523 0.1551 1.0000 17.000 1.1967 0.06181 0.05504 0.0529 0.1507 1.0000 17.250 1.1938 0.06426 0.05750 0.0534 0.1457 1.0000 17.500 1.1934 0.06646 0.05970 0.0539 0.1409 1.0000 17.750 1.1864 0.06956 0.06291 0.0541 0.1355 1.0000 18.000 1.1866 0.07172 0.06497 0.0545 0.1301 1.0000 18.250 1.1768 0.07535 0.06875 0.0544 0.1248 1.0000 18.500 1.1772 0.07756 0.07084 0.0546 0.1196 1.0000 18.750 1.1675 0.08132 0.07476 0.0543 0.1146 1.0000 19.000 1.1653 0.08406 0.07748 0.0541 0.1104 1.0000 19.250 1.1632 0.08682 0.08027 0.0540 0.1064 1.0000