XFOIL Version 6.96 Calculated polar for: GOE 8K AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.3485 0.02991 0.02679 -0.2352 0.9101 0.0062 -13.750 -0.3673 0.02711 0.02375 -0.2327 0.9033 0.0063 -13.500 -0.3709 0.02535 0.02181 -0.2304 0.8985 0.0064 -13.250 -0.3750 0.02346 0.01969 -0.2278 0.8942 0.0064 -13.000 -0.3867 0.02277 0.01893 -0.2213 0.8899 0.0064 -12.750 -0.4011 0.02172 0.01775 -0.2145 0.8853 0.0067 -12.500 -0.3981 0.02072 0.01660 -0.2110 0.8821 0.0068 -12.250 -0.3840 0.01976 0.01551 -0.2097 0.8796 0.0069 -12.000 -0.3891 0.01913 0.01480 -0.2038 0.8762 0.0070 -11.750 -0.3896 0.01849 0.01407 -0.1987 0.8726 0.0071 -11.500 -0.3792 0.01787 0.01335 -0.1960 0.8698 0.0074 -11.250 -0.3659 0.01718 0.01254 -0.1938 0.8674 0.0074 -11.000 -0.3476 0.01654 0.01177 -0.1927 0.8653 0.0077 -10.750 -0.3385 0.01603 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0.00930 0.00303 -0.1194 0.7574 0.0507 -1.000 0.3655 0.00926 0.00298 -0.1181 0.7549 0.0512 -0.750 0.3871 0.00922 0.00292 -0.1170 0.7523 0.0514 -0.500 0.4101 0.00921 0.00289 -0.1162 0.7500 0.0521 -0.250 0.4344 0.00917 0.00283 -0.1157 0.7480 0.0527 0.000 0.4556 0.00918 0.00283 -0.1145 0.7461 0.0530 0.250 0.4757 0.00918 0.00285 -0.1131 0.7440 0.0535 0.500 0.4971 0.00919 0.00286 -0.1119 0.7418 0.0541 0.750 0.5186 0.00921 0.00288 -0.1109 0.7392 0.0546 1.000 0.5403 0.00924 0.00289 -0.1098 0.7356 0.0549 1.250 0.5651 0.00925 0.00288 -0.1095 0.7332 0.0559 1.500 0.5861 0.00929 0.00294 -0.1083 0.7307 0.0561 1.750 0.6052 0.00935 0.00301 -0.1067 0.7273 0.0564 2.000 0.6265 0.00939 0.00306 -0.1056 0.7243 0.0595 2.250 0.6490 0.00942 0.00312 -0.1048 0.7218 0.0659 2.500 0.6728 0.00946 0.00317 -0.1042 0.7194 0.0678 2.750 0.6997 0.00929 0.00330 -0.1047 0.7166 0.2070 3.250 1.0466 0.00858 0.00474 -0.1750 0.7186 1.0000 3.500 1.0620 0.00872 0.00489 -0.1726 0.7136 1.0000 3.750 1.0771 0.00888 0.00505 -0.1702 0.7078 1.0000 4.000 1.0866 0.00914 0.00529 -0.1665 0.6987 1.0000 4.250 1.0964 0.00942 0.00553 -0.1629 0.6885 1.0000 4.500 1.1164 0.00955 0.00568 -0.1616 0.6859 1.0000 4.750 1.1302 0.00978 0.00593 -0.1590 0.6775 1.0000 5.000 1.1414 0.01009 0.00623 -0.1558 0.6682 1.0000 5.250 1.1513 0.01045 0.00656 -0.1524 0.6562 1.0000 5.500 1.1650 0.01076 0.00688 -0.1498 0.6454 1.0000 5.750 1.1525 0.01177 0.00772 -0.1418 0.6054 1.0000 6.000 1.1227 0.01350 0.00915 -0.1306 0.5466 1.0000 6.250 1.1188 0.01457 0.01007 -0.1249 0.5152 1.0000 6.500 1.1141 0.01575 0.01109 -0.1192 0.4816 1.0000 6.750 1.0970 0.01752 0.01256 -0.1114 0.4231 1.0000 7.000 1.1080 0.01819 0.01317 -0.1088 0.4059 1.0000 7.250 1.1072 0.01941 0.01422 -0.1043 0.3673 1.0000 7.500 1.1025 0.02085 0.01542 -0.0992 0.3171 1.0000 7.750 1.0978 0.02237 0.01668 -0.0942 0.2649 1.0000 8.000 1.0971 0.02375 0.01782 -0.0901 0.2208 1.0000 8.250 1.1016 0.02491 0.01882 -0.0869 0.1867 1.0000 8.500 1.1052 0.02613 0.01985 -0.0836 0.1493 1.0000 8.750 1.1043 0.02765 0.02112 -0.0797 0.0991 1.0000 9.000 1.1133 0.02866 0.02203 -0.0774 0.0784 1.0000 9.250 1.1249 0.02953 0.02286 -0.0755 0.0673 1.0000 9.500 1.1368 0.03039 0.02370 -0.0737 0.0572 1.0000 9.750 1.1466 0.03140 0.02462 -0.0716 0.0400 1.0000 10.000 1.1570 0.03237 0.02554 -0.0696 0.0284 1.0000 10.250 1.1683 0.03332 0.02647 -0.0678 0.0220 1.0000 10.500 1.1808 0.03419 0.02735 -0.0663 0.0192 1.0000 10.750 1.1941 0.03503 0.02820 -0.0648 0.0169 1.0000 11.000 1.2055 0.03601 0.02919 -0.0632 0.0149 1.0000 11.250 1.2183 0.03690 0.03011 -0.0617 0.0131 1.0000 11.500 1.2311 0.03780 0.03102 -0.0603 0.0121 1.0000 11.750 1.2433 0.03874 0.03199 -0.0589 0.0114 1.0000 12.000 1.2550 0.03973 0.03301 -0.0574 0.0105 1.0000 12.250 1.2669 0.04071 0.03402 -0.0560 0.0098 1.0000 12.500 1.2774 0.04180 0.03515 -0.0545 0.0091 1.0000 12.750 1.2885 0.04289 0.03627 -0.0530 0.0089 1.0000 13.000 1.3002 0.04393 0.03736 -0.0517 0.0083 1.0000 13.250 1.3113 0.04501 0.03847 -0.0504 0.0078 1.0000 13.500 1.3207 0.04625 0.03976 -0.0489 0.0078 1.0000 13.750 1.3298 0.04750 0.04104 -0.0474 0.0071 1.0000 14.000 1.3397 0.04871 0.04230 -0.0461 0.0068 1.0000 14.250 1.3490 0.04999 0.04365 -0.0447 0.0064 1.0000 14.500 1.3578 0.05132 0.04502 -0.0434 0.0060 1.0000 14.750 1.3659 0.05272 0.04645 -0.0420 0.0055 1.0000 15.000 1.3730 0.05423 0.04802 -0.0406 0.0054 1.0000 15.250 1.3799 0.05577 0.04961 -0.0392 0.0053 1.0000 15.500 1.3867 0.05736 0.05126 -0.0379 0.0052 1.0000 15.750 1.3950 0.05879 0.05276 -0.0368 0.0050 1.0000 16.000 1.3999 0.06056 0.05459 -0.0354 0.0049 1.0000 16.250 1.4046 0.06238 0.05648 -0.0341 0.0045 1.0000 16.500 1.4122 0.06394 0.05811 -0.0331 0.0046 1.0000 16.750 1.4166 0.06584 0.06007 -0.0320 0.0044 1.0000 17.000 1.4193 0.06795 0.06226 -0.0307 0.0043 1.0000 17.250 1.4228 0.06998 0.06434 -0.0297 0.0041 1.0000 17.500 1.4239 0.07229 0.06672 -0.0285 0.0040 1.0000 17.750 1.4252 0.07462 0.06913 -0.0275 0.0040 1.0000 18.000 1.4257 0.07705 0.07164 -0.0265 0.0039 1.0000 18.250 1.4296 0.07916 0.07384 -0.0259 0.0038 1.0000 18.500 1.4283 0.08189 0.07666 -0.0251 0.0038 1.0000 18.750 1.4300 0.08431 0.07917 -0.0244 0.0036 1.0000 19.000 1.4290 0.08710 0.08205 -0.0239 0.0036 1.0000