XFOIL Version 6.96 Calculated polar for: GOE 435 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.1789 0.11140 0.10470 -0.0784 0.8664 0.1133 -13.250 -0.1780 0.10796 0.10125 -0.0798 0.8578 0.1192 -12.250 -0.3436 0.07052 0.06311 -0.0997 0.8353 0.1695 -12.000 -0.2865 0.07544 0.06812 -0.0963 0.8265 0.1700 -11.750 -0.2454 0.07842 0.07111 -0.0940 0.8191 0.1706 -11.500 -0.2115 0.08033 0.07306 -0.0928 0.8106 0.1717 -11.250 -0.4341 0.04907 0.04095 -0.1119 0.8081 0.1794 -11.000 -0.4610 0.04404 0.03560 -0.1153 0.8009 0.1810 -10.750 -0.4751 0.04063 0.03187 -0.1174 0.7946 0.1826 -10.500 -0.4819 0.03850 0.02956 -0.1185 0.7865 0.1838 -10.250 -0.4566 0.03827 0.02940 -0.1179 0.7800 0.1856 -10.000 -0.4386 0.03771 0.02882 -0.1175 0.7743 0.1872 -9.750 -0.4230 0.03690 0.02793 -0.1175 0.7694 0.1889 -9.500 -0.4096 0.03602 0.02702 -0.1180 0.7624 0.1905 -9.250 -0.3953 0.03512 0.02603 -0.1184 0.7557 0.1923 -9.000 -0.3797 0.03424 0.02500 -0.1186 0.7498 0.1942 -8.750 -0.3624 0.03336 0.02393 -0.1189 0.7447 0.1960 -8.500 -0.3456 0.03265 0.02309 -0.1191 0.7379 0.1975 -8.250 -0.3269 0.03202 0.02231 -0.1191 0.7307 0.1987 -8.000 -0.3034 0.03147 0.02172 -0.1190 0.7245 0.1998 -7.750 -0.2779 0.03100 0.02123 -0.1188 0.7194 0.2012 -7.500 -0.2543 0.03064 0.02090 -0.1185 0.7134 0.2029 -7.250 -0.2323 0.03031 0.02059 -0.1182 0.7062 0.2047 -7.000 -0.2085 0.02990 0.02014 -0.1182 0.6999 0.2065 -6.750 -0.1833 0.02944 0.01959 -0.1182 0.6947 0.2082 -6.500 -0.1577 0.02900 0.01906 -0.1184 0.6898 0.2099 -6.250 -0.1364 0.02871 0.01875 -0.1181 0.6820 0.2116 -6.000 -0.1120 0.02833 0.01827 -0.1181 0.6753 0.2135 -5.750 -0.0856 0.02791 0.01777 -0.1182 0.6698 0.2155 -5.500 -0.0591 0.02756 0.01745 -0.1181 0.6648 0.2177 -5.250 -0.0371 0.02739 0.01736 -0.1176 0.6571 0.2198 -5.000 -0.0119 0.02712 0.01710 -0.1175 0.6511 0.2218 -4.750 0.0153 0.02680 0.01673 -0.1176 0.6463 0.2238 -4.500 0.0433 0.02650 0.01635 -0.1178 0.6421 0.2256 -4.250 0.0655 0.02642 0.01631 -0.1173 0.6352 0.2269 -4.000 0.0911 0.02623 0.01609 -0.1172 0.6294 0.2280 -3.750 0.1188 0.02597 0.01577 -0.1173 0.6248 0.2293 -3.500 0.1483 0.02569 0.01540 -0.1176 0.6211 0.2306 -3.250 0.1700 0.02569 0.01550 -0.1170 0.6145 0.2319 -3.000 0.1952 0.02557 0.01542 -0.1169 0.6094 0.2336 -2.750 0.2228 0.02537 0.01524 -0.1171 0.6052 0.2356 -2.500 0.2524 0.02513 0.01495 -0.1175 0.6017 0.2381 -2.250 0.2778 0.02507 0.01491 -0.1175 0.5968 0.2409 -2.000 0.3022 0.02507 0.01495 -0.1173 0.5914 0.2441 -1.750 0.3295 0.02495 0.01485 -0.1175 0.5870 0.2481 -1.500 0.3596 0.02468 0.01460 -0.1181 0.5828 0.2541 -1.250 0.3880 0.02449 0.01443 -0.1184 0.5777 0.2623 -1.000 0.4112 0.02449 0.01459 -0.1181 0.5704 0.2739 -0.750 0.4400 0.02436 0.01458 -0.1184 0.5647 0.2931 -0.500 0.4720 0.02429 0.01454 -0.1189 0.5603 0.3193 -0.250 0.4956 0.02458 0.01487 -0.1185 0.5547 0.3414 0.000 0.5208 0.02483 0.01511 -0.1182 0.5494 0.3581 0.250 0.5491 0.02497 0.01519 -0.1183 0.5447 0.3715 0.500 0.5810 0.02501 0.01505 -0.1190 0.5407 0.3845 0.750 0.6069 0.02527 0.01535 -0.1186 0.5362 0.3926 1.000 0.6286 0.02564 0.01572 -0.1179 0.5306 0.4011 1.250 0.6544 0.02584 0.01589 -0.1177 0.5255 0.4090 1.500 0.6830 0.02597 0.01601 -0.1177 0.5211 0.4167 1.750 0.7165 0.02601 0.01589 -0.1184 0.5171 0.4253 2.000 0.7329 0.02649 0.01643 -0.1171 0.5112 0.4310 2.250 0.7539 0.02677 0.01679 -0.1162 0.5056 0.4353 2.500 0.7804 0.02692 0.01693 -0.1159 0.5006 0.4407 2.750 0.8126 0.02695 0.01686 -0.1165 0.4963 0.4477 3.000 0.8303 0.02739 0.01732 -0.1153 0.4905 0.4530 3.250 0.8470 0.02780 0.01778 -0.1139 0.4843 0.4573 3.500 0.8703 0.02797 0.01799 -0.1133 0.4788 0.4619 3.750 0.9010 0.02800 0.01796 -0.1136 0.4741 0.4676 4.000 0.9129 0.02855 0.01859 -0.1116 0.4679 0.4722 4.250 0.9219 0.02906 0.01917 -0.1092 0.4611 0.4762 4.500 0.9440 0.02925 0.01929 -0.1085 0.4554 0.4803 4.750 0.9713 0.02932 0.01929 -0.1084 0.4504 0.4845 5.000 0.9698 0.03043 0.02061 -0.1052 0.4426 0.4878 5.250 0.9859 0.03093 0.02116 -0.1040 0.4360 0.4928 5.500 1.0148 0.03090 0.02104 -0.1040 0.4310 0.4995 5.750 1.0098 0.03253 0.02284 -0.1012 0.4222 0.5036 6.000 1.0256 0.03316 0.02344 -0.1002 0.4155 0.5092 6.250 1.0407 0.03379 0.02413 -0.0991 0.4093 0.5142 6.500 1.0416 0.03537 0.02584 -0.0972 0.4008 0.5183 6.750 1.0621 0.03573 0.02616 -0.0966 0.3950 0.5244 7.000 1.0632 0.03753 0.02805 -0.0951 0.3868 0.5291 7.250 1.0757 0.03856 0.02905 -0.0943 0.3801 0.5344 7.500 1.0925 0.03924 0.02974 -0.0936 0.3745 0.5393 7.750 1.0935 0.04124 0.03185 -0.0923 0.3668 0.5434 8.000 1.1120 0.04185 0.03242 -0.0917 0.3615 0.5492 8.250 1.1227 0.04318 0.03375 -0.0910 0.3556 0.5553 8.500 1.1276 0.04506 0.03566 -0.0901 0.3491 0.5615 8.750 1.1469 0.04559 0.03619 -0.0896 0.3445 0.5686 9.000 1.1619 0.04660 0.03720 -0.0890 0.3398 0.5770 9.250 1.1622 0.04898 0.03968 -0.0880 0.3338 0.5849 9.500 1.1761 0.05007 0.04080 -0.0874 0.3292 0.5942 9.750 1.2019 0.05008 0.04074 -0.0871 0.3256 0.6075 10.000 1.2022 0.05254 0.04332 -0.0862 0.3206 0.6184 10.250 1.2045 0.05483 0.04574 -0.0854 0.3157 0.6313 10.500 1.2181 0.05600 0.04695 -0.0848 0.3119 0.6483 10.750 1.2428 0.05605 0.04699 -0.0843 0.3089 0.6709 11.000 1.2519 0.05770 0.04871 -0.0836 0.3052 0.6925 11.250 1.2403 0.06149 0.05271 -0.0828 0.3003 0.7092 11.500 1.2455 0.06357 0.05487 -0.0821 0.2964 0.7323 11.750 1.2625 0.06436 0.05568 -0.0816 0.2933 0.7599 12.000 1.2886 0.06409 0.05538 -0.0809 0.2910 0.7906 12.250 1.2859 0.06695 0.05839 -0.0801 0.2876 0.8152 12.500 1.2505 0.07370 0.06546 -0.0796 0.2823 0.8313 12.750 1.2420 0.07659 0.06854 -0.0783 0.2786 0.8970 13.000 1.2568 0.07735 0.06926 -0.0779 0.2761 1.0000 13.250 1.2859 0.07702 0.06881 -0.0778 0.2742 1.0000 13.750 1.1509 0.10133 0.09376 -0.0810 0.2588 1.0000 14.000 1.1795 0.10078 0.09312 -0.0807 0.2577 1.0000 14.250 1.2123 0.09962 0.09185 -0.0803 0.2568 1.0000 14.500 1.2480 0.09808 0.09020 -0.0798 0.2560 1.0000 15.000 0.9311 0.15820 0.15137 -0.1000 0.2173 1.0000 15.250 0.9400 0.16080 0.15395 -0.1013 0.2148 1.0000