XFOIL Version 6.96 Calculated polar for: GOE 398 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.3094 0.10964 0.10588 -0.0463 1.0000 0.0281 -11.250 -0.3164 0.10600 0.10229 -0.0464 1.0000 0.0285 -10.750 -0.5187 0.04558 0.04137 -0.0988 0.9661 0.0302 -10.500 -0.5097 0.04216 0.03777 -0.1019 0.9563 0.0305 -10.250 -0.4979 0.03934 0.03474 -0.1038 0.9470 0.0311 -10.000 -0.4851 0.03667 0.03181 -0.1051 0.9375 0.0318 -9.750 -0.4697 0.03333 0.02804 -0.1069 0.9302 0.0328 -9.500 -0.4605 0.03007 0.02419 -0.1066 0.9196 0.0339 -9.250 -0.4374 0.02788 0.02163 -0.1075 0.9137 0.0347 -9.000 -0.4134 0.02691 0.02059 -0.1075 0.9059 0.0353 -8.750 -0.3862 0.02595 0.01951 -0.1081 0.8992 0.0363 -8.500 -0.3595 0.02473 0.01805 -0.1086 0.8928 0.0375 -8.250 -0.3374 0.02348 0.01649 -0.1080 0.8840 0.0386 -8.000 -0.3095 0.02221 0.01491 -0.1084 0.8779 0.0395 -7.750 -0.2865 0.02152 0.01420 -0.1077 0.8693 0.0403 -7.500 -0.2591 0.02085 0.01345 -0.1078 0.8626 0.0414 -7.250 -0.2338 0.02019 0.01266 -0.1074 0.8554 0.0426 -7.000 -0.2092 0.01947 0.01176 -0.1068 0.8475 0.0438 -6.750 -0.1815 0.01874 0.01083 -0.1067 0.8412 0.0448 -6.500 -0.1592 0.01817 0.01024 -0.1057 0.8323 0.0459 -6.250 -0.1323 0.01770 0.00971 -0.1054 0.8250 0.0473 -6.000 -0.1087 0.01727 0.00921 -0.1045 0.8160 0.0488 -5.750 -0.0828 0.01678 0.00859 -0.1039 0.8075 0.0504 -5.500 -0.0593 0.01632 0.00806 -0.1030 0.7985 0.0518 -5.250 -0.0344 0.01593 0.00763 -0.1023 0.7902 0.0534 -5.000 -0.0102 0.01561 0.00726 -0.1014 0.7814 0.0556 -4.750 0.0148 0.01530 0.00683 -0.1006 0.7726 0.0583 -4.500 0.0388 0.01496 0.00650 -0.0997 0.7644 0.0611 -4.250 0.0633 0.01468 0.00618 -0.0989 0.7567 0.0645 -4.000 0.0887 0.01440 0.00584 -0.0982 0.7503 0.0687 -3.750 0.1126 0.01417 0.00560 -0.0973 0.7423 0.0744 -3.500 0.1379 0.01392 0.00532 -0.0966 0.7354 0.0818 -3.250 0.1622 0.01370 0.00510 -0.0957 0.7280 0.0902 -3.000 0.1871 0.01350 0.00489 -0.0950 0.7209 0.1008 -2.750 0.2123 0.01329 0.00471 -0.0943 0.7142 0.1158 -2.500 0.2362 0.01310 0.00460 -0.0934 0.7062 0.1367 -2.250 0.2618 0.01295 0.00449 -0.0927 0.6992 0.1641 -2.000 0.2861 0.01284 0.00443 -0.0919 0.6913 0.1922 -1.750 0.3109 0.01269 0.00433 -0.0912 0.6840 0.2183 -1.500 0.3352 0.01256 0.00424 -0.0903 0.6763 0.2446 -1.250 0.3590 0.01239 0.00416 -0.0894 0.6680 0.2762 -1.000 0.3822 0.01218 0.00412 -0.0884 0.6601 0.3311 -0.750 0.4041 0.01195 0.00412 -0.0871 0.6515 0.4073 -0.500 0.4259 0.01173 0.00410 -0.0857 0.6434 0.4883 -0.250 0.4461 0.01148 0.00413 -0.0839 0.6341 0.5752 0.000 0.4666 0.01110 0.00416 -0.0820 0.6255 0.7045 0.500 0.6340 0.01104 0.00437 -0.1049 0.5984 0.9872 0.750 0.6741 0.01118 0.00439 -0.1075 0.5856 1.0000 1.000 0.6949 0.01130 0.00439 -0.1060 0.5732 1.0000 1.250 0.7154 0.01143 0.00442 -0.1044 0.5595 1.0000 1.500 0.7357 0.01157 0.00446 -0.1028 0.5443 1.0000 1.750 0.7556 0.01173 0.00451 -0.1011 0.5285 1.0000 2.000 0.7754 0.01191 0.00457 -0.0994 0.5131 1.0000 2.250 0.7950 0.01211 0.00466 -0.0976 0.4982 1.0000 2.500 0.8144 0.01233 0.00476 -0.0959 0.4848 1.0000 2.750 0.8335 0.01257 0.00488 -0.0941 0.4723 1.0000 3.000 0.8532 0.01280 0.00503 -0.0925 0.4607 1.0000 3.250 0.8730 0.01304 0.00520 -0.0908 0.4504 1.0000 3.500 0.8924 0.01331 0.00537 -0.0892 0.4410 1.0000 3.750 0.9127 0.01355 0.00556 -0.0877 0.4323 1.0000 4.000 0.9323 0.01382 0.00577 -0.0861 0.4242 1.0000 4.250 0.9527 0.01407 0.00598 -0.0846 0.4167 1.0000 4.500 0.9728 0.01432 0.00620 -0.0831 0.4094 1.0000 4.750 0.9923 0.01461 0.00644 -0.0815 0.4026 1.0000 5.000 1.0124 0.01485 0.00668 -0.0801 0.3951 1.0000 5.250 1.0310 0.01516 0.00693 -0.0784 0.3878 1.0000 5.500 1.0506 0.01541 0.00720 -0.0768 0.3805 1.0000 5.750 1.0688 0.01569 0.00747 -0.0751 0.3729 1.0000 6.000 1.0872 0.01599 0.00776 -0.0733 0.3663 1.0000 6.250 1.1052 0.01627 0.00806 -0.0715 0.3589 1.0000 6.500 1.1206 0.01660 0.00835 -0.0693 0.3522 1.0000 6.750 1.1374 0.01687 0.00866 -0.0673 0.3449 1.0000 7.000 1.1522 0.01720 0.00899 -0.0650 0.3377 1.0000 7.250 1.1678 0.01753 0.00934 -0.0629 0.3303 1.0000 7.500 1.1825 0.01789 0.00971 -0.0607 0.3222 1.0000 7.750 1.1974 0.01828 0.01010 -0.0585 0.3146 1.0000 8.000 1.2110 0.01871 0.01054 -0.0563 0.3054 1.0000 8.250 1.2247 0.01917 0.01100 -0.0541 0.2960 1.0000 8.500 1.2364 0.01972 0.01151 -0.0518 0.2870 1.0000 8.750 1.2502 0.02024 0.01205 -0.0498 0.2773 1.0000 9.000 1.2618 0.02087 0.01266 -0.0476 0.2691 1.0000 9.250 1.2752 0.02147 0.01328 -0.0458 0.2609 1.0000 9.500 1.2868 0.02217 0.01397 -0.0438 0.2544 1.0000 9.750 1.3009 0.02280 0.01466 -0.0422 0.2477 1.0000 10.000 1.3119 0.02360 0.01545 -0.0403 0.2412 1.0000 10.250 1.3246 0.02435 0.01624 -0.0387 0.2346 1.0000 10.500 1.3359 0.02519 0.01711 -0.0370 0.2281 1.0000 10.750 1.3462 0.02612 0.01805 -0.0353 0.2222 1.0000 11.000 1.3589 0.02696 0.01897 -0.0339 0.2168 1.0000 11.250 1.3688 0.02798 0.02001 -0.0324 0.2114 1.0000 11.500 1.3791 0.02900 0.02109 -0.0310 0.2060 1.0000 11.750 1.3904 0.03001 0.02217 -0.0297 0.2007 1.0000 12.000 1.3987 0.03122 0.02342 -0.0283 0.1957 1.0000 12.250 1.4082 0.03239 0.02467 -0.0270 0.1903 1.0000 12.500 1.4157 0.03374 0.02608 -0.0258 0.1832 1.0000 12.750 1.4216 0.03525 0.02762 -0.0246 0.1769 1.0000 13.000 1.4285 0.03673 0.02918 -0.0235 0.1693 1.0000 13.250 1.4326 0.03848 0.03098 -0.0224 0.1629 1.0000 13.500 1.4379 0.04021 0.03279 -0.0214 0.1546 1.0000 13.750 1.4408 0.04220 0.03484 -0.0205 0.1458 1.0000 14.000 1.4407 0.04454 0.03721 -0.0197 0.1348 1.0000 14.250 1.4373 0.04730 0.03997 -0.0190 0.1192 1.0000 14.500 1.4269 0.05089 0.04350 -0.0184 0.1020 1.0000 14.750 1.4145 0.05486 0.04743 -0.0180 0.0897 1.0000 15.250 1.3935 0.06287 0.05549 -0.0179 0.0770 1.0000 15.500 1.3841 0.06695 0.05964 -0.0182 0.0738 1.0000 15.750 1.3747 0.07118 0.06395 -0.0186 0.0711 1.0000 16.000 1.3669 0.07531 0.06819 -0.0192 0.0690 1.0000 16.250 1.3578 0.07970 0.07267 -0.0200 0.0671 1.0000 16.500 1.3470 0.08442 0.07749 -0.0209 0.0655 1.0000 16.750 1.3363 0.08919 0.08235 -0.0221 0.0642 1.0000