XFOIL Version 6.96 Calculated polar for: GOE 449 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.6107 0.06864 0.06516 -0.1178 0.9752 0.0272 -15.750 -0.6522 0.05669 0.05295 -0.1283 0.9703 0.0273 -15.500 -0.6717 0.04850 0.04453 -0.1364 0.9632 0.0274 -15.250 -0.6760 0.04192 0.03771 -0.1446 0.9576 0.0275 -15.000 -0.6727 0.03709 0.03268 -0.1512 0.9508 0.0277 -14.750 -0.6594 0.03363 0.02909 -0.1568 0.9446 0.0279 -14.500 -0.6385 0.03083 0.02616 -0.1623 0.9394 0.0282 -14.250 -0.6186 0.02879 0.02398 -0.1659 0.9304 0.0284 -14.000 -0.5967 0.02702 0.02207 -0.1691 0.9219 0.0286 -13.750 -0.5796 0.02571 0.02064 -0.1703 0.9112 0.0289 -13.500 -0.5654 0.02463 0.01943 -0.1703 0.9010 0.0292 -13.250 -0.5530 0.02366 0.01833 -0.1697 0.8910 0.0295 -13.000 -0.5446 0.02285 0.01740 -0.1678 0.8813 0.0296 -12.750 -0.5339 0.02213 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-3.250 0.2422 0.01075 0.00341 -0.1201 0.6852 0.0909 -3.000 0.2663 0.01069 0.00332 -0.1193 0.6796 0.0954 -2.750 0.2901 0.01058 0.00323 -0.1185 0.6743 0.1013 -2.500 0.3138 0.01051 0.00316 -0.1176 0.6678 0.1076 -2.250 0.3365 0.01042 0.00308 -0.1165 0.6610 0.1169 -2.000 0.3595 0.01034 0.00302 -0.1155 0.6538 0.1270 -1.750 0.3817 0.01028 0.00296 -0.1144 0.6458 0.1377 -1.500 0.4040 0.01020 0.00292 -0.1132 0.6384 0.1518 -1.250 0.4253 0.01014 0.00287 -0.1119 0.6295 0.1689 -1.000 0.4462 0.01007 0.00285 -0.1105 0.6207 0.1898 -0.750 0.4657 0.01002 0.00283 -0.1088 0.6108 0.2143 -0.500 0.4860 0.00997 0.00282 -0.1073 0.6018 0.2397 0.000 0.5220 0.00987 0.00282 -0.1033 0.5838 0.3002 0.250 0.5369 0.00980 0.00283 -0.1007 0.5753 0.3419 0.500 0.5536 0.00964 0.00289 -0.0986 0.5678 0.4192 0.750 0.5696 0.00958 0.00294 -0.0962 0.5605 0.4803 1.000 0.5866 0.00951 0.00301 -0.0941 0.5541 0.5305 1.250 0.5976 0.00924 0.00315 -0.0907 0.5481 0.6676 1.500 0.6117 0.00920 0.00328 -0.0878 0.5421 0.7363 1.750 0.6268 0.00911 0.00347 -0.0850 0.5370 0.8219 2.000 0.6530 0.00917 0.00371 -0.0845 0.5314 0.9025 2.250 0.6948 0.00939 0.00393 -0.0875 0.5257 0.9442 2.500 0.7443 0.00963 0.00413 -0.0923 0.5203 0.9627 2.750 0.7887 0.00984 0.00431 -0.0960 0.5140 0.9723 3.000 0.8241 0.01010 0.00449 -0.0979 0.5064 0.9804 3.250 0.8611 0.01029 0.00465 -0.1001 0.4998 0.9860 3.500 0.8955 0.01049 0.00482 -0.1018 0.4935 0.9932 4.000 0.9461 0.01086 0.00512 -0.1015 0.4846 1.0000 4.250 0.9590 0.01096 0.00522 -0.0987 0.4807 1.0000 4.500 0.9730 0.01109 0.00534 -0.0961 0.4766 1.0000 4.750 0.9867 0.01127 0.00549 -0.0935 0.4718 1.0000 5.000 1.0022 0.01146 0.00566 -0.0913 0.4675 1.0000 5.250 1.0188 0.01163 0.00583 -0.0894 0.4612 1.0000 5.500 1.0333 0.01188 0.00605 -0.0871 0.4546 1.0000 5.750 1.0494 0.01212 0.00627 -0.0851 0.4492 1.0000 6.000 1.0672 0.01233 0.00650 -0.0835 0.4432 1.0000 6.250 1.0826 0.01263 0.00677 -0.0814 0.4370 1.0000 6.500 1.0996 0.01291 0.00704 -0.0797 0.4315 1.0000 6.750 1.1172 0.01318 0.00732 -0.0782 0.4248 1.0000 7.000 1.1310 0.01358 0.00769 -0.0761 0.4175 1.0000 7.250 1.1480 0.01391 0.00802 -0.0745 0.4086 1.0000 7.500 1.1610 0.01440 0.00846 -0.0724 0.3993 1.0000 7.750 1.1769 0.01481 0.00887 -0.0707 0.3899 1.0000 8.000 1.1898 0.01536 0.00939 -0.0687 0.3794 1.0000 8.250 1.2011 0.01601 0.00998 -0.0665 0.3675 1.0000 8.500 1.2134 0.01665 0.01059 -0.0646 0.3548 1.0000 8.750 1.2260 0.01731 0.01122 -0.0628 0.3436 1.0000 9.000 1.2375 0.01806 0.01194 -0.0609 0.3335 1.0000 9.250 1.2506 0.01876 0.01261 -0.0592 0.3232 1.0000 9.500 1.2622 0.01955 0.01338 -0.0575 0.3132 1.0000 9.750 1.2728 0.02044 0.01424 -0.0557 0.3031 1.0000 10.000 1.2854 0.02125 0.01504 -0.0542 0.2935 1.0000 10.250 1.2959 0.02220 0.01596 -0.0525 0.2845 1.0000 10.500 1.3078 0.02309 0.01686 -0.0511 0.2756 1.0000 10.750 1.3181 0.02411 0.01786 -0.0495 0.2674 1.0000 11.000 1.3295 0.02510 0.01885 -0.0482 0.2591 1.0000 11.250 1.3394 0.02619 0.01993 -0.0467 0.2520 1.0000 11.500 1.3508 0.02723 0.02098 -0.0454 0.2444 1.0000 11.750 1.3582 0.02854 0.02227 -0.0439 0.2357 1.0000 12.000 1.3673 0.02979 0.02352 -0.0426 0.2268 1.0000 12.250 1.3746 0.03118 0.02490 -0.0412 0.2191 1.0000 12.500 1.3824 0.03258 0.02630 -0.0399 0.2101 1.0000 12.750 1.3901 0.03401 0.02773 -0.0386 0.2043 1.0000 13.000 1.3983 0.03543 0.02917 -0.0375 0.1958 1.0000 13.250 1.4028 0.03718 0.03090 -0.0362 0.1869 1.0000 13.500 1.4077 0.03894 0.03265 -0.0350 0.1774 1.0000 13.750 1.4127 0.04073 0.03444 -0.0339 0.1689 1.0000 14.000 1.4145 0.04281 0.03650 -0.0327 0.1590 1.0000 14.250 1.4184 0.04477 0.03847 -0.0317 0.1514 1.0000 14.500 1.4206 0.04693 0.04062 -0.0307 0.1442 1.0000 14.750 1.4234 0.04906 0.04275 -0.0299 0.1377 1.0000 15.000 1.4262 0.05123 0.04495 -0.0291 0.1332 1.0000 15.250 1.4294 0.05340 0.04715 -0.0284 0.1280 1.0000 15.500 1.4312 0.05574 0.04951 -0.0277 0.1237 1.0000 15.750 1.4333 0.05810 0.05191 -0.0271 0.1197 1.0000 16.000 1.4381 0.06020 0.05407 -0.0267 0.1166 1.0000 16.250 1.4406 0.06256 0.05646 -0.0262 0.1135 1.0000 16.500 1.4412 0.06515 0.05908 -0.0258 0.1106 1.0000 16.750 1.4444 0.06747 0.06146 -0.0255 0.1078 1.0000 17.000 1.4473 0.06986 0.06392 -0.0253 0.1043 1.0000 17.250 1.4503 0.07225 0.06636 -0.0251 0.1018 1.0000 17.500 1.4464 0.07544 0.06956 -0.0249 0.0973 1.0000 17.750 1.4514 0.07762 0.07182 -0.0248 0.0955 1.0000 18.000 1.4530 0.08022 0.07447 -0.0247 0.0915 1.0000 18.250 1.4520 0.08313 0.07741 -0.0247 0.0877 1.0000 18.500 1.4525 0.08590 0.08024 -0.0248 0.0839 1.0000 18.750 1.4505 0.08900 0.08336 -0.0250 0.0785 1.0000 19.000 1.4473 0.09222 0.08662 -0.0252 0.0737 1.0000 19.250 1.4419 0.09577 0.09018 -0.0255 0.0686 1.0000