XFOIL Version 6.96 Calculated polar for: GOE 228 (MVA H.38) 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.4264 0.09326 0.09031 -0.0990 0.9649 0.0219 -15.500 -0.4625 0.08280 0.07968 -0.1057 0.9575 0.0221 -15.250 -0.4824 0.07571 0.07246 -0.1102 0.9492 0.0223 -15.000 -0.4976 0.06968 0.06631 -0.1140 0.9407 0.0224 -14.750 -0.5083 0.06452 0.06105 -0.1175 0.9310 0.0226 -14.500 -0.5174 0.05982 0.05622 -0.1206 0.9216 0.0228 -14.250 -0.5247 0.05546 0.05176 -0.1237 0.9113 0.0230 -14.000 -0.5307 0.05142 0.04759 -0.1267 0.9015 0.0232 -13.750 -0.5349 0.04764 0.04368 -0.1296 0.8916 0.0235 -13.500 -0.5366 0.04405 0.03997 -0.1326 0.8819 0.0237 -13.250 -0.5364 0.04067 0.03644 -0.1356 0.8732 0.0240 -13.000 -0.5332 0.03748 0.03312 -0.1388 0.8643 0.0243 -12.750 -0.5289 0.03451 0.02998 -0.1418 0.8564 0.0247 -12.500 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0.7514 0.0347 -7.750 0.0011 0.01373 0.00731 -0.1808 0.7452 0.0354 -7.500 0.0307 0.01339 0.00691 -0.1814 0.7383 0.0363 -7.250 0.0603 0.01310 0.00655 -0.1820 0.7315 0.0373 -7.000 0.0900 0.01282 0.00621 -0.1825 0.7232 0.0384 -6.750 0.1194 0.01258 0.00588 -0.1830 0.7149 0.0393 -6.500 0.1492 0.01228 0.00554 -0.1836 0.7052 0.0407 -6.250 0.1785 0.01206 0.00525 -0.1841 0.6948 0.0423 -6.000 0.2076 0.01189 0.00499 -0.1844 0.6828 0.0442 -5.750 0.2368 0.01171 0.00476 -0.1848 0.6700 0.0468 -5.500 0.2656 0.01158 0.00456 -0.1851 0.6568 0.0508 -5.250 0.2941 0.01148 0.00440 -0.1853 0.6428 0.0565 -5.000 0.3225 0.01141 0.00426 -0.1855 0.6287 0.0630 -4.750 0.3507 0.01138 0.00413 -0.1857 0.6147 0.0689 -4.500 0.3792 0.01133 0.00401 -0.1859 0.6013 0.0747 -4.250 0.4075 0.01131 0.00391 -0.1860 0.5892 0.0797 -4.000 0.4357 0.01128 0.00381 -0.1862 0.5775 0.0856 -3.750 0.4641 0.01124 0.00371 -0.1864 0.5659 0.0934 -3.500 0.4926 0.01116 0.00363 -0.1867 0.5554 0.1093 -3.250 0.5211 0.01105 0.00356 -0.1871 0.5452 0.1433 -3.000 0.5500 0.01092 0.00349 -0.1876 0.5368 0.1783 -2.750 0.5785 0.01083 0.00350 -0.1879 0.5281 0.2260 -2.500 0.6068 0.01085 0.00354 -0.1881 0.5203 0.2558 -2.250 0.6346 0.01092 0.00359 -0.1882 0.5119 0.2750 -2.000 0.6623 0.01101 0.00365 -0.1882 0.5045 0.2879 -1.750 0.6902 0.01110 0.00369 -0.1882 0.4969 0.2953 -1.250 0.7455 0.01129 0.00380 -0.1882 0.4843 0.3109 -1.000 0.7730 0.01138 0.00387 -0.1882 0.4780 0.3174 -0.750 0.7999 0.01151 0.00395 -0.1881 0.4722 0.3247 -0.500 0.8276 0.01160 0.00401 -0.1881 0.4666 0.3310 -0.250 0.8546 0.01171 0.00410 -0.1881 0.4603 0.3375 0.000 0.8809 0.01185 0.00421 -0.1879 0.4538 0.3453 0.250 0.9079 0.01196 0.00430 -0.1878 0.4468 0.3536 0.500 0.9337 0.01212 0.00442 -0.1875 0.4397 0.3612 0.750 0.9602 0.01226 0.00453 -0.1873 0.4343 0.3683 1.000 0.9868 0.01236 0.00465 -0.1872 0.4292 0.3754 1.250 1.0125 0.01252 0.00478 -0.1869 0.4242 0.3820 1.750 1.0644 0.01279 0.00505 -0.1865 0.4156 0.3962 2.000 1.0897 0.01295 0.00520 -0.1861 0.4104 0.4052 2.250 1.1136 0.01315 0.00539 -0.1856 0.4047 0.4148 2.750 1.1633 0.01346 0.00574 -0.1848 0.3942 0.4385 3.000 1.1861 0.01366 0.00596 -0.1840 0.3894 0.4540 3.250 1.2081 0.01385 0.00618 -0.1831 0.3855 0.4736 3.500 1.2310 0.01400 0.00641 -0.1823 0.3817 0.4978 3.750 1.2536 0.01421 0.00667 -0.1815 0.3776 0.5225 4.000 1.2759 0.01447 0.00695 -0.1807 0.3738 0.5433 4.250 1.2975 0.01477 0.00726 -0.1798 0.3702 0.5592 4.500 1.3211 0.01499 0.00752 -0.1793 0.3673 0.5727 4.750 1.3441 0.01524 0.00781 -0.1787 0.3640 0.5841 5.000 1.3663 0.01552 0.00811 -0.1779 0.3606 0.5941 5.250 1.3876 0.01585 0.00846 -0.1771 0.3573 0.6043 5.500 1.4082 0.01621 0.00883 -0.1761 0.3541 0.6139 5.750 1.4300 0.01652 0.00917 -0.1753 0.3515 0.6237 6.000 1.4521 0.01682 0.00952 -0.1747 0.3488 0.6324 6.250 1.4734 0.01715 0.00990 -0.1739 0.3458 0.6411 6.500 1.4941 0.01752 0.01031 -0.1730 0.3428 0.6494 6.750 1.5137 0.01794 0.01076 -0.1720 0.3399 0.6593 7.000 1.5328 0.01840 0.01125 -0.1710 0.3371 0.6697 7.250 1.5534 0.01879 0.01170 -0.1702 0.3349 0.6810 7.500 1.5740 0.01917 0.01216 -0.1694 0.3324 0.6935 7.750 1.5939 0.01958 0.01265 -0.1686 0.3295 0.7092 8.000 1.6126 0.02006 0.01322 -0.1676 0.3255 0.7359 8.250 1.6241 0.02029 0.01378 -0.1652 0.3221 1.0000 8.500 1.6415 0.02090 0.01441 -0.1641 0.3191 1.0000 8.750 1.6608 0.02142 0.01497 -0.1633 0.3164 1.0000 9.000 1.6793 0.02199 0.01558 -0.1624 0.3135 1.0000 9.250 1.6967 0.02263 0.01626 -0.1614 0.3104 1.0000 9.500 1.7126 0.02338 0.01702 -0.1603 0.3070 1.0000 9.750 1.7266 0.02424 0.01789 -0.1589 0.3031 1.0000 10.000 1.7436 0.02494 0.01863 -0.1580 0.2982 1.0000 10.250 1.7568 0.02589 0.01960 -0.1567 0.2917 1.0000 10.500 1.7688 0.02695 0.02066 -0.1552 0.2859 1.0000 10.750 1.7829 0.02787 0.02162 -0.1541 0.2795 1.0000 11.000 1.7916 0.02919 0.02293 -0.1525 0.2721 1.0000 11.250 1.8007 0.03052 0.02427 -0.1509 0.2611 1.0000 11.500 1.8042 0.03232 0.02602 -0.1490 0.2460 1.0000 11.750 1.7903 0.03562 0.02915 -0.1457 0.2114 1.0000 12.000 1.7645 0.04015 0.03348 -0.1418 0.1782 1.0000 12.250 1.7603 0.04295 0.03629 -0.1399 0.1701 1.0000 12.500 1.7571 0.04575 0.03912 -0.1381 0.1639 1.0000 12.750 1.7581 0.04824 0.04166 -0.1368 0.1603 1.0000 13.000 1.7577 0.05094 0.04442 -0.1356 0.1569 1.0000 13.250 1.7557 0.05387 0.04741 -0.1343 0.1538 1.0000 13.500 1.7531 0.05694 0.05054 -0.1332 0.1510 1.0000 13.750 1.7524 0.05985 0.05353 -0.1323 0.1486 1.0000 14.000 1.7548 0.06247 0.05624 -0.1316 0.1464 1.0000 14.250 1.7545 0.06543 0.05929 -0.1308 0.1439 1.0000 14.500 1.7524 0.06865 0.06260 -0.1302 0.1416 1.0000 14.750 1.7466 0.07233 0.06635 -0.1295 0.1389 1.0000 15.000 1.7382 0.07639 0.07048 -0.1288 0.1361 1.0000 15.250 1.7328 0.08013 0.07430 -0.1284 0.1335 1.0000 15.500 1.7330 0.08318 0.07745 -0.1280 0.1309 1.0000 15.750 1.7286 0.08686 0.08120 -0.1277 0.1267 1.0000 16.000 1.7176 0.09139 0.08579 -0.1275 0.1220 1.0000 16.250 1.7107 0.09544 0.08991 -0.1274 0.1167 1.0000 16.500 1.6974 0.10041 0.09489 -0.1274 0.1070 1.0000 16.750 1.6681 0.10767 0.10208 -0.1278 0.0872 1.0000 17.000 1.6372 0.11523 0.10956 -0.1285 0.0706 1.0000