XFOIL Version 6.96 Calculated polar for: GOE 421 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 0.0863 0.10671 0.10089 -0.1393 0.8945 0.0626 -11.250 0.0824 0.10377 0.09796 -0.1391 0.8868 0.0630 -11.000 0.0833 0.09971 0.09389 -0.1412 0.8821 0.0642 -10.750 0.0811 0.09412 0.08825 -0.1449 0.8789 0.0655 -10.500 0.0648 0.08970 0.08385 -0.1451 0.8703 0.0660 -10.250 0.0441 0.08218 0.07633 -0.1487 0.8649 0.0667 -9.750 -0.2091 0.04838 0.04197 -0.1628 0.8316 0.0668 -9.500 -0.2173 0.04726 0.04082 -0.1595 0.8224 0.0675 -9.250 -0.2035 0.04552 0.03898 -0.1599 0.8177 0.0687 -9.000 -0.1846 0.04276 0.03596 -0.1624 0.8149 0.0703 -8.750 -0.1903 0.04130 0.03429 -0.1595 0.8062 0.0712 -8.500 -0.1767 0.03909 0.03174 -0.1598 0.8013 0.0727 -8.250 -0.1520 0.03669 0.02885 -0.1618 0.7987 0.0749 -8.000 -0.1197 0.03529 0.02736 -0.1636 0.7970 0.0769 -7.750 -0.1213 0.03521 0.02726 -0.1593 0.7875 0.0780 -7.500 -0.0961 0.03419 0.02610 -0.1597 0.7840 0.0802 -7.250 -0.0656 0.03289 0.02455 -0.1611 0.7818 0.0828 -7.000 -0.0317 0.03160 0.02298 -0.1629 0.7801 0.0857 -6.750 -0.0257 0.03158 0.02299 -0.1598 0.7724 0.0875 -6.500 -0.0036 0.03107 0.02242 -0.1593 0.7676 0.0904 -6.250 0.0282 0.03018 0.02134 -0.1604 0.7652 0.0942 -6.000 0.0627 0.02927 0.02031 -0.1620 0.7634 0.0982 -5.750 0.0990 0.02849 0.01947 -0.1639 0.7619 0.1035 -5.500 0.0959 0.02903 0.01996 -0.1591 0.7521 0.1063 -5.250 0.1254 0.02845 0.01934 -0.1598 0.7490 0.1119 -5.000 0.1600 0.02780 0.01861 -0.1612 0.7468 0.1200 -4.750 0.1965 0.02722 0.01805 -0.1629 0.7452 0.1298 -4.500 0.2085 0.02756 0.01840 -0.1607 0.7389 0.1377 -4.250 0.2259 0.02782 0.01866 -0.1592 0.7329 0.1485 -4.000 0.2586 0.02765 0.01845 -0.1601 0.7303 0.1639 -3.750 0.2943 0.02744 0.01812 -0.1614 0.7284 0.1801 -3.500 0.3322 0.02717 0.01768 -0.1631 0.7269 0.1957 -3.250 0.3261 0.02843 0.01899 -0.1580 0.7168 0.2009 -3.000 0.3564 0.02833 0.01873 -0.1585 0.7137 0.2133 -2.750 0.3907 0.02806 0.01841 -0.1596 0.7116 0.2246 -2.500 0.4277 0.02768 0.01795 -0.1612 0.7100 0.2356 -2.250 0.4266 0.02891 0.01920 -0.1570 0.7008 0.2412 -2.000 0.4541 0.02890 0.01905 -0.1571 0.6971 0.2508 -1.750 0.4883 0.02853 0.01871 -0.1581 0.6947 0.2596 -1.250 0.5295 0.02894 0.01902 -0.1562 0.6831 0.2734 -1.000 0.5639 0.02838 0.01841 -0.1570 0.6788 0.2823 -0.750 0.6083 0.02736 0.01726 -0.1593 0.6758 0.2908 -0.500 0.6161 0.02800 0.01793 -0.1563 0.6666 0.2943 -0.250 0.6458 0.02768 0.01755 -0.1565 0.6615 0.2992 0.000 0.6841 0.02710 0.01686 -0.1581 0.6587 0.3052 0.250 0.7202 0.02666 0.01638 -0.1594 0.6557 0.3111 0.500 0.7139 0.02805 0.01786 -0.1545 0.6459 0.3141 0.750 0.7480 0.02766 0.01742 -0.1554 0.6425 0.3208 1.000 0.7880 0.02704 0.01674 -0.1573 0.6400 0.3283 1.250 0.7817 0.02848 0.01829 -0.1525 0.6301 0.3321 1.500 0.8123 0.02823 0.01800 -0.1529 0.6259 0.3416 1.750 0.8519 0.02758 0.01733 -0.1546 0.6229 0.3542 2.000 0.8477 0.02901 0.01883 -0.1502 0.6130 0.3625 2.250 0.8778 0.02878 0.01860 -0.1505 0.6084 0.3792 2.500 0.9171 0.02812 0.01794 -0.1522 0.6052 0.4018 2.750 0.9106 0.02971 0.01964 -0.1477 0.5949 0.4150 3.000 0.9418 0.02938 0.01937 -0.1482 0.5903 0.4438 3.250 0.9775 0.02881 0.01887 -0.1493 0.5864 0.4854 3.500 0.9723 0.03033 0.02060 -0.1451 0.5756 0.5183 3.750 0.9984 0.02908 0.02014 -0.1439 0.5713 0.8055 4.000 0.9934 0.03041 0.02152 -0.1398 0.5605 1.0000 4.250 1.0230 0.03024 0.02121 -0.1400 0.5548 1.0000 4.500 1.0289 0.03146 0.02240 -0.1375 0.5449 1.0000 4.750 1.0532 0.03157 0.02241 -0.1371 0.5381 1.0000 5.000 1.0639 0.03254 0.02335 -0.1352 0.5289 1.0000 5.250 1.0848 0.03288 0.02362 -0.1345 0.5214 1.0000 5.500 1.0990 0.03368 0.02437 -0.1331 0.5128 1.0000 5.750 1.1175 0.03419 0.02481 -0.1321 0.5047 1.0000 6.000 1.1347 0.03481 0.02539 -0.1311 0.4966 1.0000 6.250 1.1510 0.03549 0.02602 -0.1299 0.4883 1.0000 6.500 1.1723 0.03584 0.02629 -0.1293 0.4813 1.0000 6.750 1.1846 0.03685 0.02728 -0.1279 0.4726 1.0000 7.000 1.2138 0.03664 0.02694 -0.1280 0.4672 1.0000 7.250 1.2185 0.03825 0.02858 -0.1259 0.4579 1.0000 7.500 1.2432 0.03837 0.02861 -0.1256 0.4522 1.0000 7.750 1.2554 0.03947 0.02971 -0.1243 0.4451 1.0000 8.000 1.2712 0.04030 0.03051 -0.1233 0.4388 1.0000 8.250 1.2981 0.04030 0.03041 -0.1233 0.4345 1.0000 8.500 1.3075 0.04170 0.03186 -0.1219 0.4285 1.0000 8.750 1.3219 0.04271 0.03288 -0.1209 0.4234 1.0000 9.000 1.3448 0.04306 0.03319 -0.1206 0.4196 1.0000 9.250 1.3713 0.04317 0.03324 -0.1206 0.4164 1.0000 9.500 1.3754 0.04504 0.03521 -0.1189 0.4114 1.0000 9.750 1.3887 0.04620 0.03641 -0.1179 0.4074 1.0000 10.000 1.4079 0.04689 0.03710 -0.1174 0.4041 1.0000 10.250 1.4339 0.04704 0.03723 -0.1174 0.4015 1.0000 10.500 1.4472 0.04820 0.03843 -0.1164 0.3978 1.0000 10.750 1.4456 0.05058 0.04093 -0.1144 0.3928 1.0000 11.000 1.4574 0.05181 0.04220 -0.1134 0.3885 1.0000 11.250 1.4803 0.05209 0.04246 -0.1132 0.3849 1.0000 11.500 1.4970 0.05294 0.04333 -0.1125 0.3815 1.0000 11.750 1.4858 0.05629 0.04686 -0.1101 0.3771 1.0000 12.000 1.4885 0.05848 0.04916 -0.1087 0.3734 1.0000 12.250 1.5020 0.05964 0.05039 -0.1080 0.3703 1.0000 12.500 1.5265 0.05975 0.05049 -0.1079 0.3676 1.0000 12.750 1.5438 0.06056 0.05133 -0.1074 0.3647 1.0000 13.000 1.5011 0.06734 0.05841 -0.1039 0.3596 1.0000 13.250 1.4866 0.07157 0.06280 -0.1022 0.3555 1.0000 13.500 1.4982 0.07298 0.06429 -0.1016 0.3526 1.0000 13.750 1.5266 0.07249 0.06381 -0.1016 0.3503 1.0000 14.000 1.5650 0.07098 0.06227 -0.1020 0.3483 1.0000 14.250 1.3763 0.09692 0.08877 -0.0970 0.3339 1.0000 14.500 1.4184 0.09411 0.08599 -0.0968 0.3329 1.0000 14.750 1.4634 0.09107 0.08294 -0.0968 0.3319 1.0000 15.000 1.5071 0.08837 0.08026 -0.0968 0.3308 1.0000 15.250 1.3390 0.11463 0.10686 -0.0966 0.3120 1.0000 15.500 1.3882 0.11032 0.10258 -0.0958 0.3129 1.0000