XFOIL Version 6.96 Calculated polar for: GOE 798 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.5638 0.08575 0.08202 -0.1168 0.9559 0.0406 -16.500 -0.6254 0.07353 0.06955 -0.1243 0.9499 0.0409 -16.250 -0.6736 0.06376 0.05958 -0.1304 0.9420 0.0411 -16.000 -0.7158 0.05472 0.05032 -0.1362 0.9340 0.0412 -15.750 -0.7469 0.04660 0.04198 -0.1422 0.9251 0.0413 -15.500 -0.7659 0.04003 0.03521 -0.1478 0.9166 0.0415 -15.250 -0.7760 0.03521 0.03022 -0.1520 0.9071 0.0417 -15.000 -0.7801 0.03203 0.02688 -0.1540 0.8985 0.0419 -14.750 -0.7797 0.02979 0.02453 -0.1546 0.8893 0.0421 -14.500 -0.7763 0.02815 0.02277 -0.1541 0.8809 0.0424 -14.250 -0.7698 0.02685 0.02137 -0.1532 0.8717 0.0427 -14.000 -0.7618 0.02579 0.02018 -0.1518 0.8627 0.0430 -13.750 -0.7526 0.02487 0.01917 -0.1502 0.8522 0.0433 -13.500 -0.7441 0.02415 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0.01203 0.00411 -0.1303 0.5696 0.1291 1.250 0.7508 0.01202 0.00414 -0.1300 0.5650 0.1323 1.500 0.7755 0.01204 0.00417 -0.1294 0.5598 0.1364 1.750 0.7989 0.01208 0.00422 -0.1286 0.5546 0.1431 2.000 0.8231 0.01207 0.00428 -0.1280 0.5496 0.1587 2.250 0.8463 0.01203 0.00437 -0.1272 0.5434 0.1952 2.500 0.8657 0.01204 0.00446 -0.1257 0.5369 0.2297 2.750 0.8858 0.01205 0.00456 -0.1243 0.5302 0.2637 3.000 0.9045 0.01209 0.00469 -0.1226 0.5217 0.3009 3.250 0.9237 0.01214 0.00486 -0.1212 0.5131 0.3566 3.500 0.9432 0.01212 0.00510 -0.1199 0.5028 0.4617 3.750 0.9620 0.01199 0.00540 -0.1185 0.4928 0.6211 4.000 0.9763 0.01190 0.00576 -0.1161 0.4815 0.7846 4.250 1.0105 0.01206 0.00624 -0.1174 0.4676 0.9947 4.500 1.0263 0.01244 0.00654 -0.1154 0.4546 1.0000 4.750 1.0383 0.01289 0.00691 -0.1127 0.4413 1.0000 5.250 1.0644 0.01390 0.00777 -0.1080 0.4146 1.0000 5.500 1.0771 0.01449 0.00828 -0.1058 0.4023 1.0000 5.750 1.0890 0.01515 0.00886 -0.1035 0.3904 1.0000 6.000 1.1040 0.01574 0.00939 -0.1017 0.3800 1.0000 6.250 1.1170 0.01644 0.01003 -0.0997 0.3709 1.0000 6.500 1.1327 0.01705 0.01060 -0.0982 0.3629 1.0000 6.750 1.1459 0.01779 0.01129 -0.0964 0.3555 1.0000 7.000 1.1626 0.01840 0.01188 -0.0951 0.3500 1.0000 7.250 1.1794 0.01902 0.01249 -0.0939 0.3449 1.0000 7.500 1.1943 0.01975 0.01320 -0.0925 0.3403 1.0000 7.750 1.2085 0.02055 0.01397 -0.0911 0.3359 1.0000 8.000 1.2267 0.02114 0.01457 -0.0902 0.3328 1.0000 8.250 1.2437 0.02181 0.01525 -0.0892 0.3295 1.0000 8.500 1.2600 0.02254 0.01598 -0.0881 0.3260 1.0000 8.750 1.2745 0.02339 0.01682 -0.0869 0.3224 1.0000 9.000 1.2884 0.02430 0.01772 -0.0857 0.3189 1.0000 9.250 1.3043 0.02511 0.01854 -0.0847 0.3163 1.0000 9.500 1.3220 0.02582 0.01929 -0.0840 0.3143 1.0000 9.750 1.3392 0.02657 0.02006 -0.0832 0.3120 1.0000 10.000 1.3551 0.02742 0.02093 -0.0824 0.3093 1.0000 10.250 1.3701 0.02834 0.02186 -0.0814 0.3065 1.0000 10.500 1.3840 0.02935 0.02287 -0.0805 0.3036 1.0000 10.750 1.3960 0.03052 0.02403 -0.0793 0.3002 1.0000 11.000 1.4120 0.03140 0.02495 -0.0786 0.2976 1.0000 11.250 1.4283 0.03228 0.02588 -0.0780 0.2954 1.0000 11.500 1.4440 0.03321 0.02685 -0.0773 0.2930 1.0000 11.750 1.4587 0.03421 0.02787 -0.0766 0.2900 1.0000 12.000 1.4714 0.03539 0.02907 -0.0757 0.2869 1.0000 12.250 1.4831 0.03665 0.03033 -0.0748 0.2838 1.0000 12.500 1.4959 0.03782 0.03152 -0.0740 0.2810 1.0000 12.750 1.5112 0.03884 0.03260 -0.0734 0.2785 1.0000 13.000 1.5254 0.03992 0.03373 -0.0728 0.2756 1.0000 13.250 1.5386 0.04109 0.03493 -0.0721 0.2723 1.0000 13.500 1.5488 0.04252 0.03638 -0.0712 0.2686 1.0000 13.750 1.5574 0.04410 0.03796 -0.0703 0.2649 1.0000 14.000 1.5718 0.04520 0.03913 -0.0698 0.2612 1.0000 14.250 1.5826 0.04664 0.04061 -0.0691 0.2564 1.0000 14.500 1.5902 0.04836 0.04234 -0.0683 0.2515 1.0000 14.750 1.5997 0.04991 0.04391 -0.0675 0.2469 1.0000 15.000 1.6080 0.05159 0.04564 -0.0668 0.2404 1.0000 15.250 1.6115 0.05375 0.04779 -0.0658 0.2331 1.0000 15.500 1.6162 0.05581 0.04987 -0.0650 0.2236 1.0000 15.750 1.6163 0.05834 0.05237 -0.0640 0.2131 1.0000 16.000 1.6127 0.06127 0.05527 -0.0629 0.2020 1.0000 16.500 1.6053 0.06722 0.06119 -0.0608 0.1842 1.0000 16.750 1.6013 0.07028 0.06424 -0.0599 0.1776 1.0000 17.000 1.6005 0.07306 0.06705 -0.0593 0.1724 1.0000 17.250 1.5965 0.07618 0.07017 -0.0585 0.1670 1.0000 17.500 1.5946 0.07913 0.07315 -0.0580 0.1627 1.0000 17.750 1.5955 0.08179 0.07584 -0.0576 0.1585 1.0000 18.000 1.5916 0.08503 0.07912 -0.0571 0.1549 1.0000 18.250 1.5894 0.08810 0.08222 -0.0568 0.1518 1.0000 18.500 1.5928 0.09056 0.08474 -0.0567 0.1496 1.0000 18.750 1.5955 0.09308 0.08732 -0.0566 0.1469 1.0000 19.000 1.5944 0.09608 0.09037 -0.0565 0.1442 1.0000 19.250 1.5920 0.09925 0.09359 -0.0565 0.1416 1.0000