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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.2923 0.13058 0.12818 -0.1201 0.9506 0.0195 -19.000 -0.2977 0.12584 0.12344 -0.1227 0.9481 0.0202 -18.750 -0.3244 0.11761 0.11514 -0.1268 0.9457 0.0211 -18.500 -0.3485 0.11011 0.10754 -0.1307 0.9432 0.0218 -18.250 -0.3680 0.10358 0.10091 -0.1342 0.9405 0.0224 -18.000 -0.3812 0.09803 0.09527 -0.1374 0.9380 0.0228 -17.750 -0.3951 0.09251 0.08970 -0.1406 0.9347 0.0232 -17.500 -0.4103 0.08693 0.08406 -0.1438 0.9311 0.0236 -17.250 -0.4243 0.08169 0.07875 -0.1469 0.9273 0.0240 -17.000 -0.4348 0.07698 0.07397 -0.1497 0.9235 0.0244 -16.750 -0.4433 0.07256 0.06950 -0.1525 0.9191 0.0248 -16.500 -0.4540 0.06795 0.06481 -0.1555 0.9137 0.0251 -16.250 -0.4606 0.06404 0.06082 -0.1579 0.9084 0.0254 -16.000 -0.4724 0.05941 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0.6734 0.0516 -6.250 0.2254 0.01030 0.00399 -0.1937 0.6683 0.0534 -6.000 0.2510 0.01020 0.00386 -0.1933 0.6621 0.0553 -5.750 0.2757 0.01014 0.00375 -0.1927 0.6562 0.0573 -5.500 0.3026 0.01005 0.00364 -0.1925 0.6517 0.0591 -5.250 0.3287 0.00994 0.00352 -0.1922 0.6468 0.0619 -5.000 0.3534 0.00989 0.00343 -0.1917 0.6414 0.0647 -4.750 0.3791 0.00982 0.00334 -0.1913 0.6365 0.0678 -4.500 0.4048 0.00973 0.00325 -0.1909 0.6312 0.0725 -4.250 0.4281 0.00968 0.00318 -0.1900 0.6254 0.0777 -4.000 0.4513 0.00962 0.00311 -0.1892 0.6203 0.0844 -3.750 0.4763 0.00953 0.00304 -0.1887 0.6152 0.0924 -3.500 0.4998 0.00948 0.00299 -0.1879 0.6090 0.1009 -3.250 0.5231 0.00944 0.00295 -0.1871 0.6031 0.1128 -3.000 0.5488 0.00934 0.00291 -0.1868 0.5973 0.1340 -2.750 0.5736 0.00932 0.00295 -0.1863 0.5917 0.1595 -2.500 0.5977 0.00938 0.00301 -0.1857 0.5868 0.1704 -2.250 0.6242 0.00942 0.00304 -0.1855 0.5824 0.1765 -2.000 0.6501 0.00947 0.00308 -0.1851 0.5773 0.1802 -1.750 0.6753 0.00956 0.00316 -0.1847 0.5723 0.1847 -1.500 0.7012 0.00964 0.00322 -0.1844 0.5680 0.1884 -1.250 0.7277 0.00971 0.00328 -0.1843 0.5634 0.1908 -1.000 0.7531 0.00983 0.00336 -0.1839 0.5579 0.1930 -0.750 0.7771 0.00996 0.00345 -0.1833 0.5525 0.1960 -0.500 0.8035 0.01002 0.00353 -0.1832 0.5475 0.2004 -0.250 0.8285 0.01013 0.00363 -0.1828 0.5413 0.2036 0.000 0.8521 0.01029 0.00376 -0.1822 0.5349 0.2063 0.250 0.8773 0.01041 0.00386 -0.1818 0.5285 0.2081 0.500 0.8998 0.01060 0.00400 -0.1810 0.5201 0.2096 0.750 0.9232 0.01078 0.00415 -0.1803 0.5118 0.2107 1.000 0.9447 0.01103 0.00433 -0.1793 0.5015 0.2115 1.250 0.9674 0.01122 0.00450 -0.1786 0.4908 0.2134 1.500 0.9879 0.01150 0.00472 -0.1775 0.4797 0.2153 2.000 1.0285 0.01211 0.00524 -0.1752 0.4552 0.2192 2.250 1.0481 0.01246 0.00553 -0.1740 0.4426 0.2211 2.500 1.0662 0.01286 0.00587 -0.1726 0.4298 0.2230 2.750 1.0840 0.01330 0.00624 -0.1711 0.4167 0.2250 3.000 1.1033 0.01369 0.00658 -0.1699 0.4045 0.2270 3.250 1.1216 0.01412 0.00697 -0.1686 0.3935 0.2290 3.750 1.1585 0.01499 0.00778 -0.1661 0.3739 0.2370 4.000 1.1763 0.01547 0.00823 -0.1648 0.3653 0.2424 4.250 1.1961 0.01587 0.00863 -0.1638 0.3588 0.2487 4.500 1.2147 0.01632 0.00909 -0.1627 0.3521 0.2603 4.750 1.2339 0.01675 0.00955 -0.1617 0.3466 0.2798 5.000 1.2542 0.01712 0.01001 -0.1610 0.3422 0.3167 5.250 1.2728 0.01760 0.01054 -0.1599 0.3369 0.3479 5.500 1.2898 0.01818 0.01113 -0.1587 0.3308 0.3689 5.750 1.3093 0.01864 0.01164 -0.1579 0.3269 0.3859 6.000 1.3276 0.01916 0.01219 -0.1569 0.3226 0.4004 6.250 1.3453 0.01974 0.01278 -0.1558 0.3183 0.4153 6.500 1.3617 0.02039 0.01347 -0.1546 0.3140 0.4335 6.750 1.3811 0.02089 0.01406 -0.1539 0.3115 0.4633 7.000 1.4037 0.02119 0.01471 -0.1539 0.3094 0.6239 7.250 1.4194 0.02113 0.01538 -0.1524 0.3074 1.0000 7.500 1.4371 0.02178 0.01604 -0.1514 0.3052 1.0000 7.750 1.4544 0.02247 0.01672 -0.1505 0.3027 1.0000 8.000 1.4707 0.02322 0.01748 -0.1494 0.3002 1.0000 8.250 1.4860 0.02405 0.01831 -0.1483 0.2974 1.0000 8.500 1.5032 0.02477 0.01904 -0.1474 0.2954 1.0000 8.750 1.5213 0.02545 0.01975 -0.1466 0.2943 1.0000 9.000 1.5387 0.02619 0.02051 -0.1458 0.2922 1.0000 9.250 1.5551 0.02698 0.02131 -0.1449 0.2888 1.0000 9.500 1.5694 0.02793 0.02227 -0.1438 0.2853 1.0000 9.750 1.5819 0.02901 0.02333 -0.1425 0.2815 1.0000 10.000 1.5967 0.02994 0.02427 -0.1415 0.2782 1.0000 10.250 1.6123 0.03084 0.02520 -0.1407 0.2752 1.0000 10.500 1.6267 0.03182 0.02619 -0.1397 0.2713 1.0000 10.750 1.6386 0.03299 0.02736 -0.1385 0.2669 1.0000 11.000 1.6496 0.03425 0.02863 -0.1373 0.2628 1.0000 11.250 1.6642 0.03524 0.02964 -0.1364 0.2586 1.0000 11.500 1.6736 0.03665 0.03104 -0.1351 0.2519 1.0000 11.750 1.6831 0.03805 0.03243 -0.1338 0.2460 1.0000 12.000 1.6883 0.03981 0.03416 -0.1321 0.2351 1.0000 12.250 1.6784 0.04282 0.03701 -0.1292 0.2070 1.0000 12.500 1.6479 0.04766 0.04162 -0.1246 0.1670 1.0000 12.750 1.6403 0.05068 0.04457 -0.1222 0.1519 1.0000 13.000 1.6399 0.05315 0.04702 -0.1205 0.1432 1.0000 13.250 1.6422 0.05541 0.04929 -0.1192 0.1362 1.0000 13.500 1.6447 0.05766 0.05154 -0.1179 0.1299 1.0000 13.750 1.6465 0.06002 0.05391 -0.1166 0.1239 1.0000 14.000 1.6475 0.06248 0.05636 -0.1153 0.1165 1.0000 14.250 1.6474 0.06511 0.05899 -0.1141 0.1099 1.0000 14.500 1.6447 0.06802 0.06187 -0.1128 0.1012 1.0000 14.750 1.6390 0.07130 0.06514 -0.1115 0.0915 1.0000 15.000 1.6255 0.07547 0.06925 -0.1099 0.0779 1.0000 15.250 1.5946 0.08174 0.07543 -0.1078 0.0549 1.0000 15.500 1.5651 0.08807 0.08173 -0.1061 0.0344 1.0000