XFOIL Version 6.96 Calculated polar for: GOE 628 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.7469 0.11104 0.10838 -0.0628 1.0000 0.0206 -18.750 -0.7891 0.10073 0.09794 -0.0690 1.0000 0.0214 -18.500 -0.8127 0.09373 0.09085 -0.0732 1.0000 0.0218 -18.250 -0.8380 0.08668 0.08373 -0.0774 1.0000 0.0228 -18.000 -0.8632 0.07987 0.07685 -0.0814 1.0000 0.0240 -17.750 -0.8817 0.07424 0.07116 -0.0847 1.0000 0.0249 -17.500 -0.8974 0.06920 0.06606 -0.0875 1.0000 0.0258 -17.250 -0.9154 0.06407 0.06088 -0.0903 1.0000 0.0265 -17.000 -0.9354 0.05903 0.05577 -0.0929 1.0000 0.0271 -16.750 -0.9600 0.05393 0.05061 -0.0954 1.0000 0.0277 -16.500 -0.9891 0.04873 0.04533 -0.0976 1.0000 0.0283 -16.000 -1.0373 0.03528 0.03165 -0.1106 0.9911 0.0288 -15.750 -1.0459 0.02589 0.02197 -0.1252 0.9799 0.0294 -15.500 -1.0269 0.02429 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0.4212 0.1871 -0.500 0.5275 0.00915 0.00219 -0.1083 0.4094 0.2049 -0.250 0.5534 0.00920 0.00223 -0.1078 0.3982 0.2179 0.000 0.5791 0.00927 0.00229 -0.1072 0.3885 0.2304 0.250 0.6046 0.00934 0.00235 -0.1066 0.3780 0.2427 0.500 0.6305 0.00942 0.00241 -0.1061 0.3695 0.2517 0.750 0.6556 0.00951 0.00249 -0.1054 0.3601 0.2646 1.000 0.6812 0.00959 0.00257 -0.1048 0.3525 0.2763 1.250 0.7063 0.00970 0.00266 -0.1042 0.3439 0.2867 1.500 0.7315 0.00979 0.00275 -0.1035 0.3373 0.2951 1.750 0.7570 0.00988 0.00283 -0.1029 0.3317 0.3029 2.000 0.7821 0.00999 0.00292 -0.1023 0.3262 0.3084 2.250 0.8069 0.01009 0.00303 -0.1016 0.3214 0.3165 2.500 0.8323 0.01017 0.00312 -0.1010 0.3176 0.3244 2.750 0.8571 0.01026 0.00322 -0.1003 0.3131 0.3337 3.000 0.8810 0.01039 0.00334 -0.0994 0.3081 0.3408 3.250 0.9052 0.01052 0.00345 -0.0986 0.3041 0.3469 3.500 0.9298 0.01059 0.00356 -0.0979 0.3014 0.3540 3.750 0.9540 0.01069 0.00367 -0.0971 0.2985 0.3609 4.000 0.9777 0.01081 0.00379 -0.0962 0.2953 0.3666 4.250 1.0002 0.01093 0.00392 -0.0951 0.2921 0.3743 4.500 1.0210 0.01107 0.00406 -0.0937 0.2885 0.3825 4.750 1.0426 0.01116 0.00418 -0.0924 0.2860 0.3901 5.000 1.0643 0.01125 0.00431 -0.0912 0.2836 0.3991 5.250 1.0858 0.01137 0.00445 -0.0899 0.2812 0.4071 5.500 1.1066 0.01151 0.00462 -0.0886 0.2787 0.4185 5.750 1.1270 0.01167 0.00480 -0.0871 0.2761 0.4300 6.000 1.1470 0.01184 0.00500 -0.0857 0.2733 0.4443 6.250 1.1663 0.01202 0.00523 -0.0841 0.2704 0.4610 6.750 1.2074 0.01223 0.00563 -0.0815 0.2666 0.5262 7.250 1.2892 0.01196 0.00633 -0.0878 0.2610 1.0000 7.500 1.3089 0.01221 0.00658 -0.0864 0.2585 1.0000 7.750 1.3275 0.01251 0.00686 -0.0849 0.2549 1.0000 8.000 1.3481 0.01275 0.00710 -0.0838 0.2527 1.0000 8.250 1.3688 0.01299 0.00736 -0.0827 0.2501 1.0000 8.500 1.3886 0.01328 0.00764 -0.0815 0.2464 1.0000 8.750 1.4072 0.01362 0.00797 -0.0801 0.2427 1.0000 9.000 1.4252 0.01400 0.00834 -0.0788 0.2394 1.0000 9.250 1.4447 0.01433 0.00869 -0.0777 0.2370 1.0000 9.500 1.4645 0.01465 0.00903 -0.0766 0.2350 1.0000 9.750 1.4840 0.01500 0.00940 -0.0756 0.2329 1.0000 10.000 1.5028 0.01539 0.00981 -0.0745 0.2304 1.0000 10.250 1.5208 0.01584 0.01027 -0.0734 0.2279 1.0000 10.500 1.5381 0.01634 0.01078 -0.0722 0.2252 1.0000 10.750 1.5548 0.01689 0.01133 -0.0710 0.2224 1.0000 11.000 1.5737 0.01733 0.01181 -0.0701 0.2202 1.0000 11.250 1.5915 0.01785 0.01236 -0.0692 0.2180 1.0000 11.500 1.6085 0.01842 0.01296 -0.0682 0.2149 1.0000 11.750 1.6239 0.01910 0.01365 -0.0671 0.2119 1.0000 12.000 1.6384 0.01986 0.01442 -0.0659 0.2088 1.0000 12.250 1.6541 0.02057 0.01515 -0.0650 0.2055 1.0000 12.500 1.6690 0.02133 0.01594 -0.0640 0.2011 1.0000 12.750 1.6791 0.02243 0.01702 -0.0627 0.1949 1.0000 13.000 1.6919 0.02339 0.01800 -0.0616 0.1902 1.0000 13.250 1.7025 0.02453 0.01914 -0.0605 0.1841 1.0000 13.500 1.7102 0.02590 0.02050 -0.0593 0.1775 1.0000 13.750 1.7177 0.02734 0.02194 -0.0581 0.1702 1.0000 14.000 1.7241 0.02891 0.02351 -0.0570 0.1647 1.0000 14.250 1.7296 0.03058 0.02518 -0.0559 0.1575 1.0000 14.500 1.7339 0.03240 0.02701 -0.0549 0.1521 1.0000 14.750 1.7374 0.03431 0.02893 -0.0539 0.1452 1.0000 15.000 1.7362 0.03669 0.03130 -0.0528 0.1374 1.0000 15.250 1.7370 0.03894 0.03356 -0.0519 0.1319 1.0000 15.500 1.7354 0.04147 0.03610 -0.0510 0.1261 1.0000 15.750 1.7330 0.04413 0.03878 -0.0503 0.1203 1.0000 16.000 1.7317 0.04673 0.04141 -0.0496 0.1166 1.0000 16.250 1.7314 0.04927 0.04399 -0.0491 0.1125 1.0000 16.500 1.7293 0.05208 0.04685 -0.0486 0.1094 1.0000 16.750 1.7227 0.05541 0.05022 -0.0482 0.1051 1.0000 17.000 1.7222 0.05812 0.05299 -0.0480 0.1029 1.0000 17.250 1.7178 0.06131 0.05622 -0.0478 0.0997 1.0000 17.500 1.7058 0.06542 0.06036 -0.0477 0.0952 1.0000 17.750 1.7036 0.06848 0.06350 -0.0477 0.0939 1.0000 18.000 1.6947 0.07233 0.06741 -0.0478 0.0903 1.0000 18.250 1.6782 0.07717 0.07228 -0.0481 0.0860 1.0000 18.500 1.6704 0.08103 0.07622 -0.0484 0.0833 1.0000 18.750 1.6603 0.08518 0.08043 -0.0488 0.0805 1.0000 19.000 1.6446 0.09010 0.08540 -0.0494 0.0775 1.0000