XFOIL Version 6.96 Calculated polar for: GOE 430 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.7922 0.11100 0.10882 -0.0523 1.0000 0.0280 -17.250 -0.8308 0.10045 0.09813 -0.0588 1.0000 0.0285 -17.000 -0.8494 0.09367 0.09133 -0.0630 1.0000 0.0292 -16.750 -0.8678 0.08692 0.08453 -0.0674 1.0000 0.0297 -16.500 -0.8885 0.07989 0.07744 -0.0720 1.0000 0.0301 -16.250 -0.9096 0.07292 0.07039 -0.0767 1.0000 0.0305 -16.000 -0.9325 0.06591 0.06329 -0.0816 1.0000 0.0309 -15.750 -0.9556 0.05924 0.05653 -0.0865 1.0000 0.0312 -15.500 -0.9785 0.05273 0.04993 -0.0914 1.0000 0.0314 -15.250 -0.9986 0.04684 0.04395 -0.0957 1.0000 0.0317 -15.000 -1.0254 0.04141 0.03843 -0.0983 1.0000 0.0318 -14.750 -1.0495 0.03629 0.03323 -0.1013 0.9978 0.0320 -14.500 -1.0226 0.03252 0.02933 -0.1095 0.9948 0.0327 -14.250 -0.9913 0.02964 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0.6577 0.00747 0.00173 -0.1575 0.5882 0.2960 0.250 0.6859 0.00754 0.00178 -0.1575 0.5736 0.3135 0.500 0.7140 0.00761 0.00183 -0.1574 0.5579 0.3298 0.750 0.7420 0.00769 0.00189 -0.1574 0.5422 0.3447 1.000 0.7699 0.00777 0.00195 -0.1574 0.5249 0.3630 1.250 0.7976 0.00786 0.00204 -0.1573 0.5056 0.3901 1.500 0.8252 0.00796 0.00215 -0.1572 0.4881 0.4259 1.750 0.8527 0.00809 0.00227 -0.1571 0.4740 0.4540 2.000 0.8804 0.00820 0.00239 -0.1570 0.4629 0.4779 2.250 0.9083 0.00829 0.00249 -0.1570 0.4542 0.4992 2.500 0.9359 0.00841 0.00261 -0.1568 0.4457 0.5171 2.750 0.9638 0.00850 0.00273 -0.1568 0.4385 0.5340 3.000 0.9911 0.00864 0.00286 -0.1566 0.4292 0.5523 3.250 1.0188 0.00874 0.00299 -0.1565 0.4214 0.5735 3.500 1.0462 0.00885 0.00314 -0.1564 0.4143 0.5957 3.750 1.0737 0.00896 0.00329 -0.1562 0.4081 0.6188 4.000 1.1013 0.00907 0.00343 -0.1561 0.4014 0.6409 4.250 1.1280 0.00924 0.00359 -0.1558 0.3937 0.6581 4.500 1.1556 0.00933 0.00372 -0.1557 0.3860 0.6742 4.750 1.1820 0.00950 0.00389 -0.1554 0.3755 0.6908 5.000 1.2084 0.00966 0.00405 -0.1551 0.3623 0.7082 5.250 1.2340 0.00988 0.00424 -0.1547 0.3411 0.7279 5.500 1.2491 0.01092 0.00485 -0.1526 0.2525 0.7518 5.750 1.2693 0.01126 0.00530 -0.1513 0.2272 0.8479 6.000 1.2887 0.01144 0.00557 -0.1495 0.2145 1.0000 6.250 1.3126 0.01181 0.00587 -0.1488 0.2049 1.0000 6.500 1.3377 0.01207 0.00612 -0.1483 0.1987 1.0000 6.750 1.3612 0.01243 0.00643 -0.1476 0.1904 1.0000 7.000 1.3862 0.01266 0.00666 -0.1471 0.1851 1.0000 7.250 1.4097 0.01300 0.00695 -0.1463 0.1771 1.0000 7.500 1.4334 0.01329 0.00723 -0.1456 0.1698 1.0000 7.750 1.4555 0.01368 0.00756 -0.1447 0.1587 1.0000 8.000 1.4766 0.01412 0.00791 -0.1436 0.1443 1.0000 8.250 1.4945 0.01473 0.00839 -0.1419 0.1218 1.0000 8.500 1.5089 0.01548 0.00899 -0.1397 0.1015 1.0000 8.750 1.5234 0.01607 0.00952 -0.1375 0.0922 1.0000 9.000 1.5398 0.01660 0.01004 -0.1356 0.0877 1.0000 9.250 1.5550 0.01719 0.01061 -0.1335 0.0827 1.0000 9.500 1.5727 0.01766 0.01111 -0.1319 0.0800 1.0000 9.750 1.5894 0.01819 0.01166 -0.1302 0.0770 1.0000 10.000 1.6035 0.01889 0.01234 -0.1282 0.0728 1.0000 10.250 1.6197 0.01947 0.01294 -0.1266 0.0681 1.0000 10.500 1.6313 0.02035 0.01376 -0.1244 0.0568 1.0000 10.750 1.6224 0.02260 0.01576 -0.1197 0.0255 1.0000 11.000 1.6291 0.02392 0.01708 -0.1172 0.0210 1.0000 11.250 1.6389 0.02507 0.01826 -0.1151 0.0190 1.0000 11.500 1.6489 0.02623 0.01946 -0.1132 0.0179 1.0000 11.750 1.6566 0.02759 0.02087 -0.1111 0.0167 1.0000 12.000 1.6662 0.02885 0.02218 -0.1093 0.0161 1.0000 12.250 1.6757 0.03014 0.02352 -0.1076 0.0156 1.0000 12.500 1.6841 0.03154 0.02498 -0.1059 0.0150 1.0000 12.750 1.6910 0.03311 0.02660 -0.1041 0.0145 1.0000 13.000 1.6957 0.03492 0.02847 -0.1023 0.0140 1.0000 13.250 1.6961 0.03716 0.03080 -0.1003 0.0135 1.0000 13.500 1.7030 0.03886 0.03256 -0.0990 0.0133 1.0000 13.750 1.7089 0.04071 0.03448 -0.0977 0.0130 1.0000 14.000 1.7137 0.04274 0.03657 -0.0964 0.0127 1.0000 14.250 1.7175 0.04491 0.03882 -0.0953 0.0124 1.0000 14.500 1.7207 0.04723 0.04120 -0.0942 0.0121 1.0000 14.750 1.7227 0.04975 0.04379 -0.0933 0.0119 1.0000 15.000 1.7227 0.05256 0.04669 -0.0924 0.0116 1.0000 15.250 1.7201 0.05576 0.04997 -0.0917 0.0114 1.0000 15.500 1.7134 0.05954 0.05385 -0.0910 0.0111 1.0000 15.750 1.7028 0.06396 0.05839 -0.0906 0.0109 1.0000 16.000 1.7025 0.06712 0.06163 -0.0904 0.0109 1.0000 16.250 1.7013 0.07043 0.06503 -0.0902 0.0107 1.0000 16.500 1.6980 0.07407 0.06876 -0.0902 0.0106 1.0000 16.750 1.6938 0.07789 0.07267 -0.0903 0.0105 1.0000 17.000 1.6890 0.08187 0.07675 -0.0906 0.0104 1.0000 17.250 1.6828 0.08609 0.08107 -0.0910 0.0102 1.0000 17.500 1.6756 0.09049 0.08557 -0.0915 0.0101 1.0000 17.750 1.6681 0.09502 0.09019 -0.0922 0.0100 1.0000 18.000 1.6602 0.09967 0.09494 -0.0930 0.0099 1.0000 18.250 1.6519 0.10443 0.09980 -0.0940 0.0098 1.0000 18.500 1.6426 0.10938 0.10484 -0.0952 0.0097 1.0000 18.750 1.6334 0.11434 0.10990 -0.0965 0.0096 1.0000 19.000 1.6244 0.11934 0.11499 -0.0980 0.0095 1.0000 19.250 1.6148 0.12450 0.12025 -0.0997 0.0094 1.0000