XFOIL Version 6.96 Calculated polar for: GOE 522 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.6724 0.08057 0.07565 -0.0893 0.9953 0.0552 -15.000 -0.7020 0.07155 0.06630 -0.0976 0.9923 0.0549 -14.750 -0.7144 0.06569 0.06022 -0.1028 0.9882 0.0548 -14.500 -0.7174 0.06106 0.05539 -0.1074 0.9839 0.0549 -14.250 -0.7108 0.05729 0.05146 -0.1119 0.9805 0.0550 -14.000 -0.7000 0.05391 0.04791 -0.1165 0.9778 0.0553 -13.750 -0.6985 0.05128 0.04516 -0.1178 0.9709 0.0556 -13.500 -0.6864 0.04863 0.04237 -0.1210 0.9668 0.0560 -13.250 -0.6665 0.04612 0.03969 -0.1250 0.9639 0.0564 -13.000 -0.6584 0.04438 0.03790 -0.1253 0.9564 0.0567 -12.750 -0.6329 0.04297 0.03652 -0.1272 0.9519 0.0572 -12.500 -0.6028 0.04134 0.03489 -0.1303 0.9489 0.0577 -12.250 -0.5830 0.03971 0.03325 -0.1323 0.9441 0.0582 -12.000 -0.5757 0.03814 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0.2985 0.01557 0.00777 -0.1221 0.6509 0.3605 -2.250 0.3228 0.01564 0.00781 -0.1213 0.6412 0.3726 -2.000 0.3460 0.01566 0.00776 -0.1202 0.6317 0.3832 -1.750 0.3728 0.01573 0.00777 -0.1199 0.6234 0.3935 -1.500 0.3937 0.01581 0.00777 -0.1185 0.6144 0.4030 -1.250 0.4229 0.01584 0.00777 -0.1186 0.6072 0.4136 -1.000 0.4445 0.01597 0.00785 -0.1173 0.5998 0.4237 -0.750 0.4681 0.01598 0.00789 -0.1164 0.5929 0.4323 -0.500 0.4989 0.01610 0.00789 -0.1169 0.5871 0.4417 -0.250 0.5211 0.01620 0.00797 -0.1158 0.5808 0.4506 0.000 0.5436 0.01625 0.00807 -0.1148 0.5745 0.4599 0.250 0.5719 0.01637 0.00808 -0.1148 0.5688 0.4706 0.500 0.5988 0.01647 0.00820 -0.1146 0.5632 0.4808 0.750 0.6186 0.01658 0.00833 -0.1130 0.5572 0.4927 1.000 0.6423 0.01663 0.00839 -0.1122 0.5510 0.5045 1.250 0.6759 0.01685 0.00846 -0.1133 0.5450 0.5204 1.500 0.6905 0.01687 0.00866 -0.1107 0.5394 0.5333 1.750 0.7112 0.01695 0.00876 -0.1093 0.5336 0.5496 2.000 0.7376 0.01707 0.00883 -0.1090 0.5280 0.5684 2.250 0.7639 0.01722 0.00902 -0.1087 0.5226 0.5877 2.500 0.7786 0.01728 0.00922 -0.1062 0.5173 0.6068 2.750 0.7991 0.01736 0.00936 -0.1047 0.5122 0.6284 3.000 0.8247 0.01747 0.00949 -0.1043 0.5077 0.6524 3.250 0.8554 0.01769 0.00972 -0.1048 0.5031 0.6794 3.500 0.8661 0.01775 0.00997 -0.1015 0.4988 0.7060 3.750 0.8816 0.01781 0.01018 -0.0991 0.4941 0.7380 4.000 0.9019 0.01786 0.01036 -0.0975 0.4897 0.7803 4.250 0.9334 0.01796 0.01055 -0.0980 0.4854 0.8425 4.500 0.9931 0.01829 0.01105 -0.1046 0.4800 0.9356 4.750 1.0267 0.01858 0.01134 -0.1064 0.4746 1.0000 5.000 1.0445 0.01879 0.01147 -0.1047 0.4701 1.0000 5.250 1.0702 0.01901 0.01158 -0.1045 0.4658 1.0000 5.500 1.0948 0.01936 0.01184 -0.1041 0.4614 1.0000 5.750 1.0977 0.01959 0.01214 -0.0997 0.4568 1.0000 6.000 1.1099 0.01983 0.01236 -0.0970 0.4519 1.0000 6.250 1.1300 0.02002 0.01248 -0.0957 0.4472 1.0000 6.500 1.1594 0.02031 0.01264 -0.0962 0.4423 1.0000 6.750 1.1583 0.02064 0.01306 -0.0913 0.4373 1.0000 7.000 1.1686 0.02092 0.01335 -0.0885 0.4319 1.0000 7.250 1.1872 0.02113 0.01349 -0.0871 0.4269 1.0000 7.500 1.2074 0.02144 0.01374 -0.0860 0.4218 1.0000 7.750 1.2090 0.02190 0.01428 -0.0820 0.4160 1.0000 8.000 1.2208 0.02222 0.01459 -0.0797 0.4103 1.0000 8.250 1.2464 0.02243 0.01465 -0.0795 0.4048 1.0000 8.500 1.2443 0.02308 0.01543 -0.0752 0.3985 1.0000 8.750 1.2524 0.02356 0.01591 -0.0726 0.3919 1.0000 9.000 1.2760 0.02381 0.01601 -0.0721 0.3860 1.0000 9.250 1.2719 0.02470 0.01703 -0.0681 0.3786 1.0000 9.500 1.2823 0.02526 0.01755 -0.0660 0.3719 1.0000 9.750 1.2944 0.02589 0.01814 -0.0642 0.3651 1.0000 10.000 1.2977 0.02681 0.01911 -0.0615 0.3575 1.0000 10.250 1.3159 0.02728 0.01945 -0.0606 0.3512 1.0000 10.500 1.3178 0.02843 0.02068 -0.0580 0.3439 1.0000 10.750 1.3273 0.02929 0.02152 -0.0562 0.3376 1.0000 11.000 1.3449 0.02993 0.02205 -0.0554 0.3320 1.0000 11.250 1.3479 0.03120 0.02341 -0.0532 0.3259 1.0000 11.500 1.3592 0.03211 0.02429 -0.0519 0.3207 1.0000 11.750 1.3838 0.03251 0.02454 -0.0518 0.3163 1.0000 12.000 1.3870 0.03393 0.02609 -0.0499 0.3121 1.0000 12.250 1.3959 0.03509 0.02731 -0.0486 0.3079 1.0000 12.500 1.4102 0.03598 0.02818 -0.0478 0.3044 1.0000 12.750 1.4344 0.03641 0.02852 -0.0477 0.3013 1.0000 13.000 1.4484 0.03743 0.02957 -0.0469 0.2982 1.0000 13.250 1.4517 0.03901 0.03126 -0.0454 0.2951 1.0000 13.500 1.4599 0.04033 0.03264 -0.0442 0.2919 1.0000 13.750 1.4723 0.04139 0.03372 -0.0434 0.2889 1.0000 14.000 1.4913 0.04209 0.03440 -0.0431 0.2865 1.0000 14.250 1.5258 0.04201 0.03420 -0.0438 0.2839 1.0000 14.500 1.5211 0.04417 0.03653 -0.0420 0.2817 1.0000 14.750 1.5190 0.04629 0.03880 -0.0405 0.2793 1.0000 15.000 1.5220 0.04813 0.04073 -0.0395 0.2768 1.0000 15.250 1.5300 0.04965 0.04231 -0.0387 0.2747 1.0000 15.500 1.5434 0.05075 0.04343 -0.0383 0.2725 1.0000 15.750 1.5634 0.05141 0.04408 -0.0381 0.2705 1.0000 16.000 1.5936 0.05146 0.04408 -0.0384 0.2687 1.0000 16.250 1.6013 0.05317 0.04588 -0.0378 0.2672 1.0000 16.500 1.5808 0.05697 0.04991 -0.0361 0.2655 1.0000 16.750 1.5609 0.06104 0.05419 -0.0348 0.2637 1.0000 17.000 1.5374 0.06567 0.05901 -0.0338 0.2613 1.0000 17.250 1.5243 0.06949 0.06297 -0.0333 0.2589 1.0000 17.500 1.5293 0.07156 0.06509 -0.0331 0.2570 1.0000 17.750 1.5484 0.07221 0.06575 -0.0330 0.2554 1.0000 18.000 1.5844 0.07118 0.06466 -0.0331 0.2539 1.0000 18.250 1.5966 0.07265 0.06617 -0.0330 0.2518 1.0000 18.500 0.9451 0.17389 0.16858 -0.0610 0.2094 1.0000 18.750 0.9663 0.17361 0.16831 -0.0606 0.2073 1.0000