XFOIL Version 6.96 Calculated polar for: GOE 626 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.6012 0.10868 0.10372 -0.0632 1.0000 0.0365 -16.000 -0.6320 0.09976 0.09460 -0.0680 1.0000 0.0366 -15.750 -0.6469 0.09407 0.08878 -0.0708 1.0000 0.0367 -15.500 -0.6577 0.08929 0.08388 -0.0729 1.0000 0.0368 -15.250 -0.6656 0.08513 0.07963 -0.0747 1.0000 0.0370 -15.000 -0.6726 0.08128 0.07569 -0.0762 1.0000 0.0372 -14.750 -0.6765 0.07807 0.07240 -0.0772 1.0000 0.0374 -14.500 -0.6810 0.07491 0.06916 -0.0780 1.0000 0.0376 -14.250 -0.6772 0.07327 0.06755 -0.0775 1.0000 0.0379 -14.000 -0.6725 0.07186 0.06617 -0.0768 1.0000 0.0383 -13.750 -0.6702 0.07018 0.06451 -0.0762 1.0000 0.0385 -13.500 -0.6690 0.06855 0.06290 -0.0755 1.0000 0.0388 -13.250 -0.6694 0.06684 0.06119 -0.0747 1.0000 0.0390 -13.000 -0.6719 0.06508 0.05944 -0.0737 1.0000 0.0392 -12.750 -0.6758 0.06343 0.05780 -0.0725 1.0000 0.0394 -12.500 -0.6821 0.06178 0.05616 -0.0710 1.0000 0.0396 -12.250 -0.6694 0.05966 0.05402 -0.0732 0.9977 0.0399 -12.000 -0.6524 0.05733 0.05166 -0.0766 0.9939 0.0403 -11.750 -0.6382 0.05506 0.04936 -0.0795 0.9897 0.0408 -11.500 -0.6247 0.05273 0.04699 -0.0825 0.9848 0.0412 -11.250 -0.6082 0.05032 0.04454 -0.0863 0.9807 0.0416 -11.000 -0.6007 0.04785 0.04202 -0.0888 0.9727 0.0421 -10.750 -0.5869 0.04511 0.03922 -0.0931 0.9673 0.0425 -10.500 -0.5854 0.04201 0.03612 -0.0962 0.9568 0.0430 -10.250 -0.5731 0.03825 0.03231 -0.1022 0.9493 0.0436 -10.000 -0.5574 0.03425 0.02820 -0.1088 0.9414 0.0443 -9.750 -0.5283 0.03017 0.02397 -0.1171 0.9378 0.0452 -9.500 -0.5107 0.02701 0.02064 -0.1210 0.9293 0.0461 -9.250 -0.4808 0.02496 0.01844 -0.1247 0.9253 0.0473 -9.000 -0.4477 0.02326 0.01663 -0.1283 0.9225 0.0489 -8.750 -0.4181 0.02192 0.01522 -0.1306 0.9186 0.0515 -8.500 -0.3949 0.02088 0.01413 -0.1311 0.9117 0.0552 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0.01528 0.00599 -0.1301 0.5040 0.3097 1.500 0.7324 0.01533 0.00604 -0.1294 0.4942 0.3117 1.750 0.7572 0.01542 0.00609 -0.1286 0.4853 0.3140 2.000 0.7821 0.01550 0.00616 -0.1279 0.4762 0.3164 2.250 0.8068 0.01560 0.00622 -0.1272 0.4684 0.3186 2.500 0.8318 0.01569 0.00631 -0.1265 0.4602 0.3207 2.750 0.8560 0.01583 0.00638 -0.1256 0.4527 0.3228 3.000 0.8809 0.01594 0.00648 -0.1249 0.4451 0.3248 3.250 0.9052 0.01605 0.00660 -0.1241 0.4382 0.3269 3.500 0.9292 0.01618 0.00674 -0.1233 0.4316 0.3291 3.750 0.9534 0.01630 0.00690 -0.1225 0.4243 0.3319 4.000 0.9767 0.01648 0.00706 -0.1215 0.4176 0.3348 4.250 1.0008 0.01664 0.00724 -0.1207 0.4116 0.3380 4.500 1.0246 0.01680 0.00743 -0.1199 0.4053 0.3409 4.750 1.0475 0.01700 0.00761 -0.1189 0.3993 0.3437 5.000 1.0705 0.01716 0.00782 -0.1179 0.3928 0.3466 5.250 1.0919 0.01733 0.00803 -0.1167 0.3843 0.3497 5.500 1.1126 0.01755 0.00826 -0.1153 0.3763 0.3531 5.750 1.1336 0.01773 0.00850 -0.1140 0.3681 0.3570 6.000 1.1527 0.01798 0.00872 -0.1123 0.3612 0.3610 6.250 1.1735 0.01816 0.00899 -0.1110 0.3545 0.3656 6.500 1.1923 0.01838 0.00927 -0.1093 0.3474 0.3708 6.750 1.2103 0.01865 0.00957 -0.1076 0.3403 0.3771 7.250 1.2450 0.01925 0.01025 -0.1039 0.3228 0.3911 7.500 1.2628 0.01955 0.01063 -0.1022 0.3137 0.4004 7.750 1.2788 0.01992 0.01104 -0.1003 0.3061 0.4116 8.000 1.2967 0.02025 0.01148 -0.0987 0.2973 0.4277 8.250 1.3121 0.02068 0.01196 -0.0968 0.2887 0.4502 8.500 1.3288 0.02107 0.01248 -0.0951 0.2785 0.4874 8.750 1.3436 0.02149 0.01308 -0.0933 0.2671 0.5603 9.250 1.3678 0.02228 0.01438 -0.0890 0.2399 1.0000 9.750 1.3861 0.02408 0.01607 -0.0844 0.2125 1.0000 10.000 1.3943 0.02511 0.01706 -0.0822 0.2010 1.0000 10.250 1.4014 0.02623 0.01815 -0.0800 0.1917 1.0000 10.500 1.4080 0.02745 0.01933 -0.0778 0.1836 1.0000 10.750 1.4149 0.02870 0.02058 -0.0758 0.1772 1.0000 11.000 1.4219 0.03000 0.02189 -0.0740 0.1714 1.0000 11.250 1.4267 0.03150 0.02340 -0.0721 0.1665 1.0000 11.500 1.4346 0.03284 0.02479 -0.0706 0.1622 1.0000 11.750 1.4413 0.03433 0.02632 -0.0691 0.1575 1.0000 12.000 1.4443 0.03616 0.02816 -0.0675 0.1529 1.0000 12.250 1.4495 0.03788 0.02995 -0.0663 0.1489 1.0000 12.500 1.4568 0.03951 0.03165 -0.0652 0.1444 1.0000 12.750 1.4597 0.04158 0.03377 -0.0641 0.1394 1.0000 13.000 1.4622 0.04378 0.03602 -0.0632 0.1351 1.0000 13.250 1.4687 0.04568 0.03801 -0.0625 0.1291 1.0000 13.500 1.4693 0.04826 0.04063 -0.0619 0.1232 1.0000 13.750 1.4730 0.05060 0.04305 -0.0614 0.1152 1.0000 14.000 1.4720 0.05353 0.04601 -0.0611 0.1059 1.0000 14.250 1.4673 0.05698 0.04946 -0.0610 0.0959 1.0000 14.500 1.4612 0.06071 0.05318 -0.0611 0.0889 1.0000 14.750 1.4552 0.06452 0.05701 -0.0613 0.0841 1.0000 15.000 1.4495 0.06840 0.06093 -0.0617 0.0810 1.0000 15.250 1.4448 0.07225 0.06484 -0.0621 0.0787 1.0000 15.500 1.4415 0.07598 0.06865 -0.0627 0.0771 1.0000 15.750 1.4375 0.07988 0.07263 -0.0634 0.0756 1.0000 16.000 1.4330 0.08394 0.07676 -0.0642 0.0743 1.0000 16.250 1.4280 0.08815 0.08105 -0.0652 0.0731 1.0000 16.500 1.4230 0.09242 0.08539 -0.0663 0.0721 1.0000