XFOIL Version 6.96 Calculated polar for: GOE 433 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9639 0.10400 0.10120 -0.0533 1.0000 0.0437 -19.000 -0.9781 0.09819 0.09532 -0.0569 1.0000 0.0443 -18.750 -0.9917 0.09254 0.08959 -0.0603 1.0000 0.0449 -18.500 -1.0064 0.08680 0.08375 -0.0639 1.0000 0.0453 -18.250 -1.0207 0.08115 0.07799 -0.0674 1.0000 0.0457 -18.000 -1.0330 0.07613 0.07295 -0.0706 1.0000 0.0465 -17.750 -1.0462 0.07093 0.06770 -0.0740 1.0000 0.0471 -17.500 -1.0600 0.06567 0.06237 -0.0774 1.0000 0.0476 -17.250 -1.0726 0.06061 0.05725 -0.0808 1.0000 0.0481 -17.000 -1.0837 0.05581 0.05237 -0.0841 1.0000 0.0486 -16.750 -1.0944 0.05120 0.04769 -0.0873 1.0000 0.0491 -16.500 -1.1025 0.04696 0.04336 -0.0903 1.0000 0.0496 -16.250 -1.1075 0.04312 0.03944 -0.0930 1.0000 0.0501 -16.000 -1.1101 0.03960 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3.500 1.0227 0.00925 0.00336 -0.1395 0.4122 0.5120 3.750 1.0506 0.00939 0.00350 -0.1394 0.4037 0.5189 4.000 1.0777 0.00959 0.00365 -0.1392 0.3942 0.5254 4.250 1.1053 0.00974 0.00379 -0.1391 0.3849 0.5316 4.500 1.1322 0.00993 0.00396 -0.1389 0.3757 0.5384 4.750 1.1595 0.01010 0.00411 -0.1387 0.3667 0.5446 5.000 1.1861 0.01031 0.00428 -0.1384 0.3573 0.5496 5.250 1.2129 0.01049 0.00445 -0.1382 0.3477 0.5551 5.500 1.2392 0.01069 0.00463 -0.1379 0.3383 0.5606 5.750 1.2648 0.01096 0.00484 -0.1375 0.3266 0.5657 6.000 1.2906 0.01118 0.00505 -0.1372 0.3146 0.5723 6.250 1.3150 0.01149 0.00531 -0.1366 0.2995 0.5793 6.500 1.3375 0.01194 0.00564 -0.1358 0.2781 0.5859 6.750 1.3580 0.01247 0.00605 -0.1347 0.2529 0.5947 7.000 1.3742 0.01326 0.00664 -0.1329 0.2164 0.6046 7.250 1.3864 0.01424 0.00740 -0.1306 0.1784 0.6166 7.500 1.4018 0.01495 0.00802 -0.1288 0.1570 0.6323 7.750 1.4161 0.01549 0.00857 -0.1266 0.1435 0.6580 8.000 1.4319 0.01599 0.00917 -0.1248 0.1318 0.7215 8.250 1.4427 0.01619 0.00978 -0.1220 0.1208 1.0000 8.500 1.4550 0.01701 0.01049 -0.1199 0.1068 1.0000 8.750 1.4537 0.01863 0.01187 -0.1162 0.0700 1.0000 9.000 1.4610 0.01984 0.01302 -0.1138 0.0597 1.0000 9.250 1.4738 0.02078 0.01395 -0.1122 0.0572 1.0000 9.500 1.4875 0.02169 0.01487 -0.1108 0.0555 1.0000 9.750 1.5023 0.02257 0.01577 -0.1095 0.0548 1.0000 10.000 1.5164 0.02351 0.01674 -0.1083 0.0542 1.0000 10.250 1.5298 0.02454 0.01780 -0.1071 0.0537 1.0000 10.500 1.5423 0.02567 0.01896 -0.1058 0.0531 1.0000 10.750 1.5539 0.02689 0.02022 -0.1046 0.0527 1.0000 11.000 1.5645 0.02821 0.02157 -0.1034 0.0522 1.0000 11.250 1.5743 0.02964 0.02304 -0.1022 0.0518 1.0000 11.500 1.5830 0.03119 0.02463 -0.1010 0.0514 1.0000 11.750 1.5908 0.03284 0.02632 -0.0998 0.0510 1.0000 12.000 1.5977 0.03460 0.02813 -0.0986 0.0506 1.0000 12.250 1.6031 0.03655 0.03014 -0.0975 0.0502 1.0000 12.500 1.6073 0.03865 0.03230 -0.0964 0.0499 1.0000 12.750 1.6104 0.04094 0.03465 -0.0955 0.0496 1.0000 13.000 1.6132 0.04335 0.03713 -0.0946 0.0493 1.0000 13.250 1.6183 0.04557 0.03941 -0.0939 0.0493 1.0000 13.500 1.6226 0.04789 0.04179 -0.0932 0.0491 1.0000 13.750 1.6264 0.05031 0.04428 -0.0926 0.0490 1.0000 14.000 1.6296 0.05285 0.04688 -0.0921 0.0489 1.0000 14.250 1.6325 0.05545 0.04955 -0.0916 0.0487 1.0000 14.500 1.6354 0.05803 0.05218 -0.0912 0.0484 1.0000 14.750 1.6362 0.06090 0.05512 -0.0908 0.0482 1.0000 15.000 1.6372 0.06375 0.05804 -0.0904 0.0479 1.0000 15.250 1.6373 0.06676 0.06111 -0.0901 0.0477 1.0000 15.500 1.6363 0.06993 0.06434 -0.0899 0.0474 1.0000 15.750 1.6358 0.07302 0.06750 -0.0896 0.0472 1.0000 16.000 1.6333 0.07645 0.07100 -0.0896 0.0470 1.0000 16.250 1.6316 0.07980 0.07442 -0.0895 0.0467 1.0000 16.500 1.6294 0.08325 0.07793 -0.0895 0.0465 1.0000 16.750 1.6260 0.08687 0.08162 -0.0897 0.0464 1.0000 17.000 1.6239 0.09033 0.08515 -0.0898 0.0462 1.0000 17.250 1.6202 0.09408 0.08897 -0.0901 0.0460 1.0000 17.500 1.6174 0.09772 0.09267 -0.0904 0.0458 1.0000 17.750 1.6143 0.10139 0.09640 -0.0908 0.0456 1.0000 18.000 1.6103 0.10519 0.10026 -0.0913 0.0454 1.0000 18.250 1.6075 0.10884 0.10397 -0.0919 0.0451 1.0000 18.500 1.6026 0.11280 0.10799 -0.0926 0.0448 1.0000 18.750 1.5998 0.11645 0.11169 -0.0932 0.0445 1.0000