XFOIL Version 6.96 Calculated polar for: GOE 675 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.6613 0.06696 0.06432 -0.1048 0.9571 0.0288 -14.750 -0.7286 0.05393 0.05103 -0.1145 0.9394 0.0287 -14.500 -0.7835 0.04056 0.03738 -0.1274 0.9243 0.0286 -14.250 -0.8010 0.03097 0.02742 -0.1412 0.9132 0.0287 -14.000 -0.7920 0.02895 0.02521 -0.1422 0.9071 0.0288 -13.750 -0.7782 0.02744 0.02355 -0.1427 0.9019 0.0289 -13.500 -0.7713 0.02500 0.02094 -0.1429 0.8970 0.0291 -13.250 -0.7571 0.02338 0.01919 -0.1428 0.8925 0.0294 -13.000 -0.7389 0.02220 0.01790 -0.1426 0.8883 0.0296 -12.750 -0.7184 0.02125 0.01686 -0.1425 0.8841 0.0299 -12.500 -0.6963 0.02039 0.01594 -0.1424 0.8810 0.0301 -12.250 -0.6735 0.01961 0.01509 -0.1422 0.8774 0.0304 -12.000 -0.6501 0.01890 0.01429 -0.1421 0.8739 0.0306 -11.750 -0.6261 0.01824 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0.00835 0.00242 -0.1426 0.7099 0.0926 -2.000 0.4612 0.00831 0.00236 -0.1426 0.7034 0.0944 -1.750 0.4899 0.00826 0.00231 -0.1427 0.6958 0.0964 -1.500 0.5179 0.00827 0.00225 -0.1426 0.6878 0.0976 -1.250 0.5465 0.00817 0.00216 -0.1427 0.6800 0.0999 -1.000 0.5742 0.00814 0.00211 -0.1425 0.6714 0.1029 -0.750 0.6026 0.00811 0.00208 -0.1426 0.6624 0.1057 -0.500 0.6300 0.00814 0.00206 -0.1424 0.6521 0.1083 -0.250 0.6578 0.00812 0.00203 -0.1423 0.6409 0.1134 0.000 0.6851 0.00813 0.00204 -0.1421 0.6298 0.1204 0.250 0.7118 0.00816 0.00206 -0.1418 0.6169 0.1325 0.500 0.7384 0.00820 0.00209 -0.1416 0.6020 0.1495 0.750 0.7645 0.00825 0.00214 -0.1412 0.5851 0.1703 1.000 0.7896 0.00830 0.00222 -0.1407 0.5659 0.2084 1.250 0.8145 0.00836 0.00234 -0.1402 0.5447 0.2619 1.500 0.8386 0.00851 0.00247 -0.1395 0.5199 0.3001 1.750 0.8615 0.00871 0.00263 -0.1386 0.4947 0.3374 2.000 0.8850 0.00882 0.00280 -0.1379 0.4738 0.3987 2.250 0.9085 0.00878 0.00301 -0.1373 0.4579 0.5342 2.500 0.9330 0.00806 0.00330 -0.1365 0.4462 1.0000 2.750 0.9577 0.00826 0.00344 -0.1359 0.4366 1.0000 3.000 0.9820 0.00847 0.00358 -0.1353 0.4278 1.0000 3.250 1.0068 0.00866 0.00372 -0.1347 0.4206 1.0000 3.500 1.0319 0.00883 0.00385 -0.1342 0.4144 1.0000 3.750 1.0556 0.00906 0.00402 -0.1334 0.4079 1.0000 4.000 1.0807 0.00922 0.00416 -0.1329 0.4029 1.0000 4.250 1.1056 0.00939 0.00430 -0.1324 0.3975 1.0000 4.500 1.1283 0.00963 0.00449 -0.1315 0.3907 1.0000 4.750 1.1523 0.00981 0.00465 -0.1308 0.3846 1.0000 5.000 1.1757 0.00998 0.00480 -0.1300 0.3784 1.0000 5.250 1.1961 0.01024 0.00501 -0.1286 0.3721 1.0000 5.500 1.2189 0.01043 0.00519 -0.1277 0.3675 1.0000 5.750 1.2423 0.01060 0.00537 -0.1269 0.3634 1.0000 6.000 1.2643 0.01084 0.00558 -0.1259 0.3586 1.0000 6.250 1.2844 0.01116 0.00586 -0.1246 0.3525 1.0000 6.500 1.3084 0.01133 0.00605 -0.1241 0.3483 1.0000 6.750 1.3307 0.01157 0.00629 -0.1232 0.3434 1.0000 7.000 1.3512 0.01189 0.00658 -0.1221 0.3376 1.0000 7.250 1.3732 0.01216 0.00685 -0.1212 0.3320 1.0000 7.500 1.3948 0.01245 0.00713 -0.1203 0.3256 1.0000 7.750 1.4137 0.01287 0.00750 -0.1190 0.3183 1.0000 8.000 1.4361 0.01313 0.00778 -0.1183 0.3129 1.0000 8.250 1.4557 0.01354 0.00816 -0.1172 0.3054 1.0000 8.500 1.4755 0.01393 0.00855 -0.1161 0.2990 1.0000 8.750 1.4951 0.01435 0.00895 -0.1150 0.2913 1.0000 9.000 1.5133 0.01484 0.00941 -0.1138 0.2830 1.0000 9.250 1.5307 0.01539 0.00992 -0.1124 0.2730 1.0000 9.500 1.5479 0.01595 0.01045 -0.1111 0.2621 1.0000 9.750 1.5628 0.01666 0.01110 -0.1095 0.2498 1.0000 10.000 1.5765 0.01744 0.01181 -0.1078 0.2358 1.0000 10.250 1.5884 0.01834 0.01263 -0.1059 0.2199 1.0000 10.500 1.5990 0.01933 0.01353 -0.1039 0.2027 1.0000 10.750 1.6066 0.02053 0.01462 -0.1016 0.1840 1.0000 11.000 1.6129 0.02184 0.01582 -0.0992 0.1654 1.0000 11.250 1.6177 0.02328 0.01715 -0.0967 0.1459 1.0000 11.500 1.6164 0.02515 0.01886 -0.0937 0.1206 1.0000 11.750 1.6083 0.02758 0.02108 -0.0901 0.0905 1.0000 12.000 1.6014 0.03003 0.02340 -0.0869 0.0684 1.0000 12.250 1.5915 0.03286 0.02607 -0.0838 0.0437 1.0000 12.500 1.5949 0.03476 0.02796 -0.0819 0.0384 1.0000 12.750 1.6016 0.03642 0.02965 -0.0805 0.0362 1.0000 13.000 1.6084 0.03811 0.03138 -0.0792 0.0350 1.0000 13.250 1.6146 0.03991 0.03321 -0.0779 0.0339 1.0000 13.500 1.6191 0.04192 0.03527 -0.0766 0.0329 1.0000 13.750 1.6254 0.04380 0.03721 -0.0755 0.0324 1.0000 14.000 1.6319 0.04568 0.03915 -0.0745 0.0319 1.0000 14.250 1.6368 0.04777 0.04130 -0.0735 0.0315 1.0000 14.500 1.6412 0.04995 0.04354 -0.0726 0.0310 1.0000 14.750 1.6442 0.05233 0.04599 -0.0717 0.0305 1.0000 15.000 1.6452 0.05498 0.04871 -0.0709 0.0300 1.0000 15.250 1.6445 0.05785 0.05164 -0.0701 0.0296 1.0000 15.500 1.6423 0.06096 0.05483 -0.0694 0.0292 1.0000 15.750 1.6377 0.06444 0.05840 -0.0688 0.0288 1.0000 16.000 1.6314 0.06820 0.06225 -0.0683 0.0285 1.0000 16.250 1.6310 0.07127 0.06540 -0.0680 0.0283 1.0000 16.500 1.6289 0.07460 0.06882 -0.0678 0.0281 1.0000 16.750 1.6255 0.07817 0.07247 -0.0677 0.0279 1.0000 17.000 1.6212 0.08190 0.07629 -0.0678 0.0277 1.0000 17.250 1.6160 0.08581 0.08029 -0.0680 0.0275 1.0000 17.500 1.6101 0.08983 0.08441 -0.0682 0.0272 1.0000 17.750 1.6032 0.09402 0.08868 -0.0686 0.0270 1.0000 18.000 1.5961 0.09830 0.09305 -0.0691 0.0267 1.0000 18.250 1.5886 0.10267 0.09750 -0.0698 0.0265 1.0000 18.500 1.5811 0.10707 0.10198 -0.0705 0.0263 1.0000 18.750 1.5733 0.11150 0.10650 -0.0714 0.0261 1.0000 19.000 1.5649 0.11606 0.11114 -0.0724 0.0260 1.0000