XFOIL Version 6.96 Calculated polar for: GOE 679 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.7687 0.08510 0.08160 -0.0936 0.9927 0.0267 -17.500 -0.7780 0.08029 0.07673 -0.0964 0.9919 0.0268 -17.250 -0.7877 0.07560 0.07197 -0.0990 0.9907 0.0268 -17.000 -0.8042 0.07010 0.06639 -0.1025 0.9895 0.0268 -16.750 -0.8225 0.06418 0.06038 -0.1064 0.9882 0.0269 -16.500 -0.8474 0.05745 0.05354 -0.1110 0.9868 0.0269 -16.250 -0.8714 0.05049 0.04645 -0.1161 0.9854 0.0269 -16.000 -0.8907 0.04336 0.03916 -0.1222 0.9840 0.0269 -15.750 -0.8992 0.03697 0.03261 -0.1289 0.9828 0.0269 -15.500 -0.8986 0.03242 0.02791 -0.1341 0.9818 0.0270 -15.250 -0.8960 0.02859 0.02395 -0.1387 0.9808 0.0272 -15.000 -0.9088 0.02660 0.02187 -0.1362 0.9758 0.0272 -14.750 -0.9033 0.02477 0.01996 -0.1364 0.9730 0.0274 -14.500 -0.8907 0.02343 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1.500 0.4933 0.01006 0.00296 -0.0612 0.3713 0.2607 1.750 0.5150 0.01013 0.00303 -0.0598 0.3659 0.2706 2.000 0.5372 0.01017 0.00310 -0.0586 0.3617 0.2817 2.250 0.5591 0.01023 0.00317 -0.0573 0.3569 0.2927 2.500 0.5796 0.01033 0.00327 -0.0557 0.3508 0.3046 2.750 0.6016 0.01038 0.00335 -0.0545 0.3468 0.3183 3.000 0.6234 0.01044 0.00344 -0.0532 0.3412 0.3327 3.250 0.6438 0.01051 0.00355 -0.0517 0.3358 0.3538 3.500 0.6634 0.01060 0.00367 -0.0500 0.3308 0.3762 3.750 0.6836 0.01062 0.00379 -0.0485 0.3260 0.4092 4.000 0.7028 0.01065 0.00392 -0.0468 0.3207 0.4510 4.250 0.7200 0.01071 0.00408 -0.0447 0.3139 0.5055 4.500 0.7371 0.01061 0.00424 -0.0426 0.3097 0.5941 4.750 0.7521 0.01055 0.00441 -0.0400 0.3042 0.6824 5.000 0.7615 0.01039 0.00464 -0.0362 0.2988 0.8118 5.500 0.9815 0.01114 0.00556 -0.0721 0.2748 0.9981 5.750 1.0171 0.01145 0.00581 -0.0740 0.2671 1.0000 6.000 1.0331 0.01169 0.00601 -0.0718 0.2603 1.0000 6.250 1.0504 0.01193 0.00621 -0.0698 0.2539 1.0000 6.500 1.0666 0.01223 0.00646 -0.0677 0.2465 1.0000 6.750 1.0851 0.01245 0.00667 -0.0660 0.2426 1.0000 7.000 1.1019 0.01276 0.00694 -0.0641 0.2358 1.0000 7.250 1.1192 0.01307 0.00722 -0.0623 0.2306 1.0000 7.500 1.1382 0.01334 0.00747 -0.0609 0.2264 1.0000 7.750 1.1561 0.01365 0.00777 -0.0593 0.2219 1.0000 8.000 1.1725 0.01404 0.00812 -0.0575 0.2165 1.0000 8.250 1.1913 0.01434 0.00842 -0.0561 0.2132 1.0000 8.500 1.2103 0.01465 0.00873 -0.0547 0.2104 1.0000 8.750 1.2273 0.01505 0.00910 -0.0532 0.2060 1.0000 9.000 1.2439 0.01548 0.00952 -0.0516 0.2020 1.0000 9.250 1.2623 0.01585 0.00989 -0.0502 0.1994 1.0000 9.500 1.2803 0.01623 0.01028 -0.0489 0.1970 1.0000 9.750 1.2981 0.01664 0.01069 -0.0476 0.1945 1.0000 10.000 1.3151 0.01710 0.01115 -0.0462 0.1915 1.0000 10.250 1.3309 0.01763 0.01167 -0.0448 0.1887 1.0000 10.500 1.3471 0.01815 0.01220 -0.0434 0.1858 1.0000 10.750 1.3645 0.01863 0.01270 -0.0422 0.1837 1.0000 11.000 1.3812 0.01915 0.01324 -0.0410 0.1817 1.0000 11.250 1.3975 0.01971 0.01381 -0.0397 0.1795 1.0000 11.500 1.4127 0.02034 0.01446 -0.0384 0.1773 1.0000 11.750 1.4273 0.02103 0.01515 -0.0371 0.1748 1.0000 12.000 1.4408 0.02180 0.01593 -0.0358 0.1721 1.0000 12.250 1.4570 0.02243 0.01659 -0.0348 0.1706 1.0000 12.500 1.4719 0.02315 0.01734 -0.0336 0.1686 1.0000 12.750 1.4862 0.02392 0.01813 -0.0325 0.1663 1.0000 13.000 1.4986 0.02484 0.01906 -0.0313 0.1635 1.0000 13.250 1.5106 0.02581 0.02004 -0.0301 0.1609 1.0000 13.500 1.5223 0.02682 0.02107 -0.0290 0.1586 1.0000 13.750 1.5362 0.02770 0.02199 -0.0281 0.1571 1.0000 14.000 1.5485 0.02870 0.02303 -0.0271 0.1552 1.0000 14.250 1.5602 0.02976 0.02412 -0.0261 0.1530 1.0000 14.500 1.5704 0.03096 0.02535 -0.0251 0.1510 1.0000 14.750 1.5792 0.03229 0.02669 -0.0241 0.1485 1.0000 15.000 1.5877 0.03368 0.02812 -0.0231 0.1464 1.0000 15.250 1.5986 0.03488 0.02936 -0.0223 0.1448 1.0000 15.500 1.6074 0.03628 0.03081 -0.0215 0.1427 1.0000 15.750 1.6142 0.03786 0.03242 -0.0206 0.1394 1.0000 16.000 1.6157 0.03995 0.03450 -0.0196 0.1349 1.0000 16.250 1.6226 0.04161 0.03622 -0.0189 0.1325 1.0000 16.500 1.6279 0.04343 0.03807 -0.0183 0.1291 1.0000 16.750 1.6278 0.04579 0.04045 -0.0175 0.1252 1.0000 17.000 1.6281 0.04817 0.04286 -0.0169 0.1208 1.0000 17.250 1.6264 0.05080 0.04552 -0.0163 0.1161 1.0000 17.500 1.6240 0.05357 0.04831 -0.0159 0.1123 1.0000 17.750 1.6173 0.05682 0.05159 -0.0155 0.1063 1.0000 18.000 1.6088 0.06035 0.05515 -0.0153 0.1013 1.0000 18.250 1.5976 0.06427 0.05910 -0.0152 0.0962 1.0000 18.500 1.5872 0.06817 0.06304 -0.0153 0.0922 1.0000 18.750 1.5786 0.07193 0.06686 -0.0155 0.0896 1.0000 19.000 1.5684 0.07595 0.07093 -0.0159 0.0873 1.0000 19.250 1.5577 0.08010 0.07514 -0.0163 0.0849 1.0000