XFOIL Version 6.96 Calculated polar for: FX 60-100 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3828 0.08353 0.08132 -0.0399 1.0000 0.0078 -8.750 -0.3927 0.07889 0.07673 -0.0408 1.0000 0.0074 -8.500 -0.3973 0.07269 0.07057 -0.0450 0.9977 0.0073 -8.250 -0.4185 0.04383 0.04143 -0.0779 0.9769 0.0062 -8.000 -0.3909 0.03321 0.03020 -0.0989 0.9675 0.0062 -7.750 -0.3668 0.02776 0.02422 -0.1054 0.9597 0.0061 -7.500 -0.3393 0.02398 0.01997 -0.1092 0.9543 0.0060 -7.250 -0.3131 0.02130 0.01691 -0.1110 0.9473 0.0060 -7.000 -0.2839 0.01915 0.01440 -0.1126 0.9420 0.0061 -6.750 -0.2573 0.01760 0.01257 -0.1131 0.9344 0.0062 -6.500 -0.2289 0.01636 0.01109 -0.1137 0.9281 0.0063 -6.250 -0.2023 0.01490 0.00941 -0.1140 0.9205 0.0065 -6.000 -0.1749 0.01368 0.00805 -0.1144 0.9138 0.0068 -5.750 -0.1475 0.01292 0.00721 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0.7134 0.4358 -0.500 0.4475 0.00723 0.00130 -0.1168 0.6930 0.4528 -0.250 0.4750 0.00731 0.00131 -0.1166 0.6724 0.4661 0.000 0.5023 0.00740 0.00134 -0.1163 0.6522 0.4791 0.250 0.5295 0.00750 0.00138 -0.1161 0.6293 0.4940 0.500 0.5562 0.00766 0.00144 -0.1158 0.6005 0.5079 0.750 0.5827 0.00785 0.00152 -0.1155 0.5699 0.5184 1.000 0.6092 0.00804 0.00160 -0.1152 0.5416 0.5282 1.250 0.6361 0.00822 0.00170 -0.1150 0.5170 0.5382 1.500 0.6631 0.00837 0.00180 -0.1148 0.4961 0.5481 1.750 0.6903 0.00852 0.00190 -0.1146 0.4786 0.5584 2.000 0.7175 0.00867 0.00203 -0.1144 0.4611 0.5697 2.250 0.7444 0.00884 0.00216 -0.1143 0.4402 0.5808 2.500 0.7709 0.00906 0.00230 -0.1140 0.4147 0.5907 2.750 0.7973 0.00929 0.00246 -0.1138 0.3908 0.6009 3.250 0.8499 0.00978 0.00284 -0.1133 0.3412 0.6238 3.500 0.8761 0.01003 0.00304 -0.1130 0.3175 0.6377 4.000 0.9277 0.01059 0.00352 -0.1124 0.2682 0.6693 4.250 0.9530 0.01092 0.00379 -0.1120 0.2398 0.6873 4.500 0.9780 0.01127 0.00409 -0.1116 0.2127 0.7086 4.750 1.0020 0.01172 0.00445 -0.1111 0.1780 0.7350 5.000 1.0260 0.01211 0.00481 -0.1105 0.1486 0.7700 5.250 1.0482 0.01235 0.00515 -0.1095 0.1305 0.8336 5.500 1.0685 0.01244 0.00537 -0.1078 0.1201 1.0000 5.750 1.0936 0.01283 0.00571 -0.1075 0.1047 1.0000 6.000 1.1182 0.01327 0.00609 -0.1070 0.0928 1.0000 6.250 1.1431 0.01367 0.00646 -0.1066 0.0849 1.0000 6.500 1.1682 0.01401 0.00682 -0.1062 0.0760 1.0000 6.750 1.1924 0.01446 0.00723 -0.1057 0.0657 1.0000 7.000 1.2164 0.01492 0.00766 -0.1052 0.0593 1.0000 7.250 1.2397 0.01543 0.00816 -0.1046 0.0532 1.0000 7.500 1.2638 0.01583 0.00860 -0.1040 0.0483 1.0000 7.750 1.2868 0.01634 0.00910 -0.1034 0.0408 1.0000 8.000 1.3098 0.01683 0.00960 -0.1027 0.0366 1.0000 8.250 1.3322 0.01735 0.01012 -0.1020 0.0328 1.0000 8.500 1.3544 0.01788 0.01069 -0.1012 0.0298 1.0000 8.750 1.3765 0.01839 0.01124 -0.1004 0.0272 1.0000 9.000 1.3976 0.01897 0.01185 -0.0995 0.0244 1.0000 9.250 1.4182 0.01958 0.01248 -0.0986 0.0214 1.0000 9.500 1.4375 0.02025 0.01315 -0.0975 0.0160 1.0000 9.750 1.4510 0.02148 0.01427 -0.0956 0.0055 1.0000 10.000 1.4668 0.02242 0.01527 -0.0940 0.0041 1.0000 10.250 1.4818 0.02335 0.01629 -0.0922 0.0035 1.0000 10.500 1.4941 0.02430 0.01736 -0.0900 0.0031 1.0000 10.750 1.5061 0.02517 0.01834 -0.0878 0.0030 1.0000 11.000 1.5170 0.02612 0.01940 -0.0856 0.0028 1.0000 11.250 1.5269 0.02717 0.02056 -0.0833 0.0027 1.0000 11.500 1.5356 0.02833 0.02185 -0.0811 0.0026 1.0000 11.750 1.5434 0.02962 0.02325 -0.0789 0.0025 1.0000 12.000 1.5502 0.03103 0.02479 -0.0769 0.0024 1.0000 12.250 1.5557 0.03261 0.02651 -0.0749 0.0023 1.0000 12.500 1.5599 0.03438 0.02841 -0.0730 0.0022 1.0000 12.750 1.5628 0.03633 0.03050 -0.0713 0.0021 1.0000 13.000 1.5637 0.03858 0.03291 -0.0697 0.0021 1.0000 13.250 1.5628 0.04112 0.03560 -0.0683 0.0020 1.0000 13.500 1.5598 0.04401 0.03865 -0.0672 0.0020 1.0000 13.750 1.5547 0.04732 0.04212 -0.0665 0.0019 1.0000 14.000 1.5472 0.05114 0.04610 -0.0662 0.0019 1.0000 14.250 1.5380 0.05544 0.05057 -0.0665 0.0019 1.0000 14.500 1.5274 0.06022 0.05553 -0.0673 0.0018 1.0000 14.750 1.5156 0.06553 0.06100 -0.0688 0.0018 1.0000 15.000 1.5047 0.07105 0.06669 -0.0707 0.0018 1.0000 15.250 1.4921 0.07720 0.07301 -0.0732 0.0018 1.0000 15.500 1.4781 0.08396 0.07994 -0.0762 0.0018 1.0000 15.750 1.4619 0.09148 0.08763 -0.0799 0.0018 1.0000 16.000 1.4445 0.09959 0.09591 -0.0840 0.0018 1.0000 16.250 1.4255 0.10837 0.10486 -0.0887 0.0018 1.0000 16.500 1.4055 0.11765 0.11432 -0.0939 0.0018 1.0000