XFOIL Version 6.96 Calculated polar for: GOE 567 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.7041 0.08328 0.08032 -0.0770 1.0000 0.0296 -15.500 -0.7434 0.07385 0.07075 -0.0825 1.0000 0.0299 -15.250 -0.7733 0.06647 0.06324 -0.0867 1.0000 0.0301 -15.000 -0.7998 0.06018 0.05684 -0.0900 1.0000 0.0303 -14.750 -0.8246 0.05475 0.05133 -0.0925 1.0000 0.0305 -14.500 -0.8490 0.04981 0.04628 -0.0943 1.0000 0.0308 -14.250 -0.8735 0.04557 0.04195 -0.0950 1.0000 0.0310 -14.000 -0.9022 0.04188 0.03821 -0.0943 1.0000 0.0310 -13.750 -0.9406 0.03883 0.03514 -0.0914 1.0000 0.0309 -13.500 -0.9265 0.03308 0.02930 -0.1028 0.9939 0.0322 -13.250 -0.8954 0.02937 0.02547 -0.1120 0.9886 0.0339 -13.000 -0.8602 0.02692 0.02276 -0.1189 0.9846 0.0359 -12.750 -0.8248 0.02521 0.02105 -0.1240 0.9821 0.0379 -12.500 -0.7954 0.02431 0.02007 -0.1262 0.9763 0.0398 -12.250 -0.7609 0.02323 0.01880 -0.1294 0.9727 0.0418 -12.000 -0.7237 0.02252 0.01813 -0.1326 0.9703 0.0438 -11.750 -0.6881 0.02208 0.01763 -0.1350 0.9669 0.0458 -11.500 -0.6563 0.02147 0.01685 -0.1367 0.9611 0.0475 -11.250 -0.6207 0.02050 0.01584 -0.1395 0.9575 0.0494 -11.000 -0.5817 0.02023 0.01557 -0.1422 0.9545 0.0510 -10.750 -0.5532 0.01992 0.01520 -0.1428 0.9445 0.0527 -10.500 -0.5170 0.01945 0.01456 -0.1450 0.9383 0.0545 -10.250 -0.4896 0.01858 0.01358 -0.1457 0.9259 0.0562 -10.000 -0.4602 0.01820 0.01318 -0.1464 0.9132 0.0577 -9.750 -0.4306 0.01797 0.01289 -0.1470 0.8995 0.0592 -9.500 -0.4024 0.01770 0.01249 -0.1473 0.8849 0.0609 -9.250 -0.3752 0.01749 0.01211 -0.1474 0.8702 0.0626 -9.000 -0.3495 0.01707 0.01151 -0.1473 0.8563 0.0641 -8.750 -0.3255 0.01635 0.01074 -0.1470 0.8431 0.0659 -8.500 -0.2996 0.01611 0.01043 -0.1468 0.8316 0.0675 -8.250 -0.2736 0.01584 0.01005 -0.1466 0.8215 0.0691 -8.000 -0.2478 0.01550 0.00961 -0.1464 0.8117 0.0706 -7.750 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0.2937 0.01005 0.00309 -0.1442 0.6882 0.1271 -2.750 0.3214 0.00980 0.00296 -0.1443 0.6828 0.1552 -2.500 0.3488 0.00947 0.00284 -0.1443 0.6768 0.2130 -2.250 0.3765 0.00932 0.00277 -0.1443 0.6712 0.2572 -2.000 0.4043 0.00922 0.00276 -0.1443 0.6653 0.2902 -1.750 0.4320 0.00914 0.00274 -0.1442 0.6588 0.3159 -1.500 0.4599 0.00915 0.00272 -0.1440 0.6525 0.3372 -1.250 0.4874 0.00910 0.00272 -0.1439 0.6451 0.3557 -1.000 0.5149 0.00911 0.00270 -0.1437 0.6381 0.3728 -0.750 0.5426 0.00911 0.00273 -0.1435 0.6316 0.3888 -0.500 0.5703 0.00912 0.00276 -0.1434 0.6250 0.4041 -0.250 0.5978 0.00917 0.00278 -0.1432 0.6190 0.4174 0.000 0.6253 0.00917 0.00281 -0.1430 0.6115 0.4305 0.250 0.6525 0.00923 0.00283 -0.1428 0.6043 0.4432 0.500 0.6799 0.00925 0.00288 -0.1426 0.5973 0.4549 0.750 0.7072 0.00930 0.00293 -0.1424 0.5907 0.4666 1.000 0.7344 0.00939 0.00298 -0.1421 0.5845 0.4790 1.250 0.7616 0.00941 0.00306 -0.1419 0.5776 0.4905 1.500 0.7885 0.00950 0.00312 -0.1416 0.5714 0.5020 2.000 0.8426 0.00963 0.00330 -0.1412 0.5589 0.5256 2.250 0.8692 0.00974 0.00338 -0.1408 0.5528 0.5360 2.500 0.8962 0.00979 0.00347 -0.1406 0.5462 0.5475 2.750 0.9221 0.00988 0.00356 -0.1402 0.5388 0.5585 3.000 0.9482 0.00994 0.00365 -0.1398 0.5304 0.5702 3.500 1.0001 0.01013 0.00388 -0.1389 0.5166 0.5957 3.750 1.0257 0.01020 0.00399 -0.1385 0.5089 0.6097 4.000 1.0508 0.01030 0.00411 -0.1379 0.5012 0.6255 4.250 1.0761 0.01036 0.00424 -0.1374 0.4934 0.6441 4.500 1.1006 0.01046 0.00439 -0.1368 0.4862 0.6680 4.750 1.1254 0.01045 0.00454 -0.1362 0.4789 0.7066 5.000 1.1477 0.01011 0.00468 -0.1349 0.4717 1.0000 5.250 1.1733 0.01025 0.00482 -0.1344 0.4643 1.0000 5.500 1.1971 0.01046 0.00498 -0.1337 0.4560 1.0000 5.750 1.2218 0.01063 0.00515 -0.1331 0.4474 1.0000 6.000 1.2450 0.01085 0.00533 -0.1323 0.4395 1.0000 6.250 1.2692 0.01102 0.00552 -0.1316 0.4314 1.0000 6.500 1.2911 0.01128 0.00574 -0.1305 0.4225 1.0000 6.750 1.3138 0.01148 0.00595 -0.1296 0.4117 1.0000 7.000 1.3350 0.01175 0.00619 -0.1284 0.4012 1.0000 7.250 1.3544 0.01205 0.00646 -0.1269 0.3890 1.0000 7.500 1.3724 0.01236 0.00673 -0.1252 0.3755 1.0000 7.750 1.3884 0.01271 0.00704 -0.1230 0.3605 1.0000 8.000 1.4027 0.01313 0.00741 -0.1207 0.3442 1.0000 8.250 1.4146 0.01366 0.00786 -0.1180 0.3234 1.0000 8.500 1.4217 0.01440 0.00846 -0.1146 0.2960 1.0000 8.750 1.4256 0.01533 0.00922 -0.1109 0.2652 1.0000 9.000 1.4264 0.01646 0.01016 -0.1069 0.2327 1.0000 9.250 1.4252 0.01777 0.01129 -0.1029 0.1994 1.0000 9.500 1.4182 0.01949 0.01277 -0.0985 0.1580 1.0000 9.750 1.4169 0.02104 0.01418 -0.0952 0.1354 1.0000 10.000 1.4228 0.02226 0.01537 -0.0928 0.1263 1.0000 10.250 1.4282 0.02359 0.01668 -0.0906 0.1188 1.0000 10.500 1.4384 0.02466 0.01780 -0.0889 0.1143 1.0000 10.750 1.4454 0.02601 0.01916 -0.0871 0.1095 1.0000 11.000 1.4522 0.02743 0.02062 -0.0854 0.1044 1.0000 11.250 1.4630 0.02861 0.02184 -0.0841 0.0993 1.0000 11.500 1.4686 0.03023 0.02347 -0.0826 0.0934 1.0000 11.750 1.4786 0.03155 0.02483 -0.0814 0.0865 1.0000 12.000 1.4829 0.03337 0.02662 -0.0800 0.0748 1.0000 12.250 1.4859 0.03537 0.02857 -0.0787 0.0684 1.0000 12.500 1.4884 0.03748 0.03068 -0.0774 0.0646 1.0000 12.750 1.4916 0.03960 0.03282 -0.0763 0.0619 1.0000 13.000 1.4956 0.04170 0.03499 -0.0753 0.0602 1.0000 13.250 1.4985 0.04395 0.03731 -0.0744 0.0587 1.0000 13.500 1.5000 0.04642 0.03985 -0.0736 0.0571 1.0000 13.750 1.5003 0.04911 0.04260 -0.0729 0.0558 1.0000 14.000 1.4992 0.05202 0.04556 -0.0723 0.0543 1.0000 14.500 1.5032 0.05738 0.05108 -0.0715 0.0517 1.0000 14.750 1.5071 0.05993 0.05372 -0.0713 0.0504 1.0000 15.000 1.5093 0.06274 0.05661 -0.0711 0.0491 1.0000 15.250 1.5092 0.06587 0.05981 -0.0711 0.0477 1.0000 15.500 1.5057 0.06952 0.06351 -0.0712 0.0460 1.0000 15.750 1.5059 0.07275 0.06683 -0.0714 0.0445 1.0000 16.000 1.5148 0.07489 0.06907 -0.0715 0.0427 1.0000 16.250 1.5200 0.07752 0.07176 -0.0717 0.0403 1.0000 16.500 1.5180 0.08120 0.07547 -0.0722 0.0379 1.0000 16.750 1.5304 0.08289 0.07722 -0.0724 0.0336 1.0000 17.000 1.5342 0.08580 0.08016 -0.0728 0.0295 1.0000 17.250 1.5358 0.08906 0.08342 -0.0734 0.0254 1.0000 17.500 1.5341 0.09283 0.08720 -0.0741 0.0228 1.0000 17.750 1.5317 0.09677 0.09119 -0.0750 0.0212 1.0000 18.000 1.5282 0.10091 0.09537 -0.0760 0.0200 1.0000 18.250 1.5237 0.10529 0.09982 -0.0772 0.0192 1.0000 18.500 1.5210 0.10942 0.10405 -0.0784 0.0185 1.0000 18.750 1.5181 0.11358 0.10830 -0.0797 0.0180 1.0000 19.000 1.5138 0.11803 0.11283 -0.0812 0.0175 1.0000 19.250 1.5090 0.12261 0.11749 -0.0828 0.0170 1.0000