XFOIL Version 6.96 Calculated polar for: GOE 405 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.1070 0.10336 0.10167 -0.0843 0.9757 0.0142 -10.500 -0.0930 0.10008 0.09839 -0.0874 0.9733 0.0150 -10.250 -0.3524 0.02283 0.02000 -0.1531 0.9218 0.0128 -10.000 -0.3335 0.02102 0.01794 -0.1531 0.9148 0.0131 -9.750 -0.3238 0.01822 0.01478 -0.1522 0.9065 0.0137 -9.500 -0.3004 0.01758 0.01406 -0.1518 0.9002 0.0142 -9.250 -0.2760 0.01716 0.01357 -0.1515 0.8940 0.0146 -9.000 -0.2526 0.01658 0.01289 -0.1510 0.8869 0.0151 -8.750 -0.2288 0.01597 0.01214 -0.1506 0.8803 0.0157 -8.500 -0.2058 0.01531 0.01132 -0.1499 0.8727 0.0162 -8.250 -0.1803 0.01499 0.01087 -0.1496 0.8658 0.0166 -8.000 -0.1610 0.01369 0.00937 -0.1486 0.8570 0.0175 -7.750 -0.1350 0.01355 0.00919 -0.1483 0.8493 0.0182 -7.500 -0.1093 0.01336 0.00894 -0.1479 0.8408 0.0189 -7.250 -0.0838 0.01309 0.00857 -0.1474 0.8320 0.0197 -7.000 -0.0578 0.01298 0.00835 -0.1471 0.8229 0.0205 -6.750 -0.0317 0.01290 0.00817 -0.1466 0.8124 0.0210 -6.500 -0.0109 0.01177 0.00686 -0.1456 0.8015 0.0223 -6.250 0.0143 0.01159 0.00661 -0.1451 0.7904 0.0231 -5.750 0.0654 0.01123 0.00606 -0.1441 0.7698 0.0251 -5.500 0.0916 0.01114 0.00588 -0.1437 0.7617 0.0259 -5.250 0.1162 0.01057 0.00517 -0.1432 0.7543 0.0269 -5.000 0.1406 0.01006 0.00457 -0.1426 0.7476 0.0282 -4.750 0.1669 0.00987 0.00435 -0.1423 0.7407 0.0294 -4.250 0.2193 0.00948 0.00382 -0.1415 0.7284 0.0315 -4.000 0.2455 0.00931 0.00358 -0.1412 0.7224 0.0323 -3.750 0.2723 0.00924 0.00347 -0.1409 0.7169 0.0329 -3.500 0.2974 0.00873 0.00287 -0.1403 0.7111 0.0347 -3.250 0.3233 0.00854 0.00262 -0.1399 0.7056 0.0362 -3.000 0.3499 0.00839 0.00244 -0.1396 0.7003 0.0377 -2.750 0.3765 0.00827 0.00228 -0.1393 0.6946 0.0393 -2.500 0.4028 0.00819 0.00214 -0.1389 0.6893 0.0405 -2.250 0.4296 0.00804 0.00197 -0.1386 0.6843 0.0428 -2.000 0.4558 0.00790 0.00182 -0.1383 0.6787 0.0479 -1.750 0.4815 0.00778 0.00171 -0.1378 0.6731 0.0628 -1.500 0.5074 0.00756 0.00166 -0.1375 0.6674 0.1081 -1.250 0.5336 0.00753 0.00165 -0.1371 0.6615 0.1244 -1.000 0.5601 0.00752 0.00163 -0.1368 0.6556 0.1352 -0.750 0.5867 0.00751 0.00162 -0.1366 0.6491 0.1446 -0.500 0.6126 0.00753 0.00162 -0.1361 0.6429 0.1541 -0.250 0.6394 0.00752 0.00162 -0.1359 0.6361 0.1627 0.000 0.6650 0.00755 0.00164 -0.1354 0.6288 0.1735 0.250 0.6915 0.00755 0.00165 -0.1352 0.6214 0.1819 0.500 0.7167 0.00760 0.00167 -0.1346 0.6133 0.1899 0.750 0.7427 0.00760 0.00168 -0.1343 0.6042 0.1990 1.000 0.7679 0.00766 0.00171 -0.1337 0.5944 0.2082 1.250 0.7922 0.00772 0.00175 -0.1330 0.5828 0.2172 1.500 0.8168 0.00778 0.00178 -0.1324 0.5702 0.2255 1.750 0.8413 0.00785 0.00183 -0.1318 0.5577 0.2350 2.000 0.8653 0.00793 0.00190 -0.1310 0.5450 0.2473 2.250 0.8890 0.00801 0.00197 -0.1302 0.5319 0.2621 2.750 0.9347 0.00816 0.00216 -0.1284 0.5050 0.3279 3.000 0.9899 0.00720 0.00256 -0.1353 0.4884 1.0000 3.250 1.0112 0.00739 0.00267 -0.1340 0.4759 1.0000 3.750 1.0550 0.00773 0.00291 -0.1317 0.4548 1.0000 4.000 1.0766 0.00792 0.00304 -0.1305 0.4456 1.0000 4.250 1.0983 0.00809 0.00318 -0.1294 0.4368 1.0000 4.500 1.1203 0.00826 0.00331 -0.1283 0.4289 1.0000 4.750 1.1417 0.00845 0.00347 -0.1271 0.4214 1.0000 5.000 1.1638 0.00861 0.00361 -0.1260 0.4149 1.0000 5.250 1.1842 0.00881 0.00378 -0.1247 0.4064 1.0000 5.500 1.2037 0.00900 0.00395 -0.1231 0.3960 1.0000 5.750 1.2219 0.00922 0.00413 -0.1213 0.3877 1.0000 6.000 1.2415 0.00941 0.00430 -0.1198 0.3777 1.0000 6.250 1.2610 0.00962 0.00449 -0.1183 0.3702 1.0000 6.500 1.2786 0.00989 0.00472 -0.1164 0.3588 1.0000 6.750 1.2974 0.01014 0.00494 -0.1149 0.3461 1.0000 7.000 1.3145 0.01046 0.00519 -0.1130 0.3313 1.0000 7.250 1.3320 0.01078 0.00547 -0.1113 0.3174 1.0000 7.500 1.3472 0.01119 0.00581 -0.1092 0.3004 1.0000 7.750 1.3613 0.01167 0.00619 -0.1069 0.2788 1.0000 8.000 1.3706 0.01238 0.00673 -0.1039 0.2498 1.0000 8.250 1.3755 0.01331 0.00744 -0.1003 0.2148 1.0000 8.500 1.3767 0.01448 0.00835 -0.0963 0.1730 1.0000 8.750 1.3612 0.01659 0.00999 -0.0901 0.0988 1.0000 9.000 1.3449 0.01895 0.01201 -0.0841 0.0315 1.0000 9.250 1.3529 0.02001 0.01302 -0.0817 0.0192 1.0000 9.500 1.3645 0.02089 0.01392 -0.0799 0.0169 1.0000 9.750 1.3757 0.02183 0.01491 -0.0780 0.0153 1.0000 10.000 1.3889 0.02265 0.01577 -0.0765 0.0144 1.0000 10.250 1.3998 0.02365 0.01682 -0.0749 0.0135 1.0000 10.500 1.4093 0.02479 0.01801 -0.0731 0.0127 1.0000 10.750 1.4164 0.02613 0.01942 -0.0712 0.0122 1.0000 11.000 1.4221 0.02762 0.02100 -0.0693 0.0116 1.0000 11.250 1.4314 0.02889 0.02232 -0.0679 0.0114 1.0000 11.500 1.4400 0.03025 0.02375 -0.0665 0.0110 1.0000 11.750 1.4473 0.03175 0.02531 -0.0651 0.0106 1.0000 12.000 1.4540 0.03334 0.02696 -0.0638 0.0102 1.0000 12.250 1.4599 0.03507 0.02875 -0.0625 0.0098 1.0000 12.500 1.4631 0.03709 0.03084 -0.0612 0.0094 1.0000 12.750 1.4583 0.03993 0.03377 -0.0596 0.0090 1.0000 13.000 1.4490 0.04337 0.03734 -0.0580 0.0089 1.0000 13.250 1.4446 0.04642 0.04049 -0.0569 0.0088 1.0000 13.500 1.4530 0.04817 0.04229 -0.0563 0.0086 1.0000 13.750 1.4531 0.05085 0.04506 -0.0555 0.0084 1.0000 14.000 1.4543 0.05349 0.04778 -0.0550 0.0082 1.0000 14.250 1.4489 0.05696 0.05135 -0.0543 0.0082 1.0000 14.500 1.4491 0.05981 0.05427 -0.0539 0.0079 1.0000 14.750 1.4458 0.06314 0.05769 -0.0536 0.0077 1.0000 15.000 1.4446 0.06630 0.06093 -0.0534 0.0075 1.0000 15.250 1.4400 0.06995 0.06466 -0.0533 0.0074 1.0000 15.500 1.4349 0.07369 0.06849 -0.0533 0.0073 1.0000 15.750 1.4298 0.07750 0.07238 -0.0534 0.0072 1.0000 16.000 1.4253 0.08131 0.07626 -0.0537 0.0071 1.0000 16.250 1.4197 0.08530 0.08034 -0.0540 0.0070 1.0000 16.500 1.4146 0.08928 0.08439 -0.0544 0.0069 1.0000 16.750 1.4101 0.09318 0.08836 -0.0549 0.0068 1.0000 17.000 1.4033 0.09743 0.09267 -0.0555 0.0067 1.0000 17.250 1.3963 0.10163 0.09694 -0.0560 0.0066 1.0000