XFOIL Version 6.96 Calculated polar for: GOE 646 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6813 0.09503 0.08985 -0.0789 1.0000 0.0500 -16.500 -0.7139 0.08682 0.08144 -0.0831 1.0000 0.0506 -16.250 -0.7232 0.08275 0.07732 -0.0846 1.0000 0.0511 -16.000 -0.7265 0.07978 0.07435 -0.0853 1.0000 0.0516 -15.750 -0.7338 0.07632 0.07087 -0.0863 1.0000 0.0522 -15.500 -0.7430 0.07278 0.06728 -0.0873 1.0000 0.0527 -15.250 -0.7542 0.06919 0.06365 -0.0881 1.0000 0.0533 -15.000 -0.7668 0.06582 0.06022 -0.0886 1.0000 0.0538 -14.750 -0.7806 0.06268 0.05703 -0.0885 1.0000 0.0544 -14.500 -0.7964 0.05972 0.05402 -0.0880 1.0000 0.0548 -14.250 -0.7947 0.05602 0.05020 -0.0914 0.9978 0.0557 -14.000 -0.7866 0.05251 0.04660 -0.0955 0.9942 0.0567 -13.750 -0.7775 0.04934 0.04340 -0.0992 0.9901 0.0576 -13.500 -0.7687 0.04615 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0.5983 0.01415 0.00541 -0.1110 0.5724 0.4085 1.250 0.6220 0.01419 0.00550 -0.1101 0.5671 0.4172 1.500 0.6461 0.01423 0.00558 -0.1093 0.5618 0.4259 1.750 0.6709 0.01429 0.00565 -0.1086 0.5566 0.4364 2.000 0.6953 0.01435 0.00574 -0.1078 0.5515 0.4472 2.250 0.7175 0.01440 0.00587 -0.1066 0.5457 0.4593 2.500 0.7406 0.01445 0.00599 -0.1056 0.5403 0.4733 2.750 0.7646 0.01452 0.00610 -0.1048 0.5353 0.4909 3.000 0.7864 0.01458 0.00626 -0.1035 0.5298 0.5119 3.250 0.8070 0.01463 0.00643 -0.1020 0.5235 0.5362 3.500 0.8285 0.01471 0.00657 -0.1007 0.5176 0.5633 3.750 0.8498 0.01480 0.00674 -0.0993 0.5120 0.5927 4.000 0.8680 0.01487 0.00693 -0.0973 0.5055 0.6204 4.250 0.8866 0.01495 0.00706 -0.0954 0.4986 0.6464 4.500 0.9039 0.01505 0.00720 -0.0932 0.4909 0.6698 4.750 0.9188 0.01515 0.00737 -0.0907 0.4814 0.6917 5.000 0.9343 0.01526 0.00754 -0.0882 0.4724 0.7163 5.250 0.9499 0.01537 0.00776 -0.0858 0.4617 0.7466 5.500 0.9698 0.01544 0.00801 -0.0842 0.4522 0.8023 5.750 1.0165 0.01558 0.00832 -0.0884 0.4398 1.0000 6.000 1.0331 0.01585 0.00858 -0.0864 0.4293 1.0000 6.250 1.0478 0.01617 0.00883 -0.0842 0.4186 1.0000 6.500 1.0621 0.01652 0.00913 -0.0819 0.4062 1.0000 6.750 1.0761 0.01691 0.00947 -0.0796 0.3940 1.0000 7.000 1.0886 0.01737 0.00986 -0.0772 0.3819 1.0000 7.250 1.1009 0.01787 0.01029 -0.0748 0.3704 1.0000 7.500 1.1144 0.01838 0.01075 -0.0727 0.3602 1.0000 7.750 1.1263 0.01898 0.01128 -0.0704 0.3510 1.0000 8.000 1.1407 0.01953 0.01180 -0.0686 0.3425 1.0000 8.250 1.1527 0.02018 0.01240 -0.0665 0.3341 1.0000 8.500 1.1661 0.02082 0.01301 -0.0646 0.3259 1.0000 8.750 1.1783 0.02153 0.01368 -0.0627 0.3179 1.0000 9.000 1.1907 0.02225 0.01438 -0.0608 0.3104 1.0000 9.250 1.2031 0.02300 0.01511 -0.0591 0.3022 1.0000 9.500 1.2137 0.02386 0.01591 -0.0571 0.2954 1.0000 9.750 1.2276 0.02458 0.01668 -0.0557 0.2881 1.0000 10.000 1.2383 0.02548 0.01756 -0.0539 0.2811 1.0000 10.250 1.2504 0.02635 0.01843 -0.0524 0.2748 1.0000 10.500 1.2634 0.02718 0.01930 -0.0510 0.2689 1.0000 10.750 1.2739 0.02817 0.02029 -0.0495 0.2630 1.0000 11.000 1.2855 0.02914 0.02127 -0.0481 0.2578 1.0000 11.250 1.2974 0.03011 0.02229 -0.0468 0.2517 1.0000 11.500 1.3058 0.03130 0.02348 -0.0453 0.2455 1.0000 11.750 1.3161 0.03243 0.02464 -0.0440 0.2397 1.0000 12.000 1.3260 0.03361 0.02587 -0.0428 0.2338 1.0000 12.250 1.3332 0.03501 0.02726 -0.0415 0.2283 1.0000 12.500 1.3427 0.03629 0.02861 -0.0404 0.2225 1.0000 12.750 1.3505 0.03774 0.03010 -0.0393 0.2165 1.0000 13.250 1.3646 0.04089 0.03331 -0.0373 0.2053 1.0000 13.500 1.3700 0.04267 0.03511 -0.0363 0.1994 1.0000 13.750 1.3749 0.04453 0.03699 -0.0355 0.1940 1.0000 14.000 1.3814 0.04633 0.03885 -0.0348 0.1884 1.0000 14.250 1.3847 0.04844 0.04098 -0.0341 0.1832 1.0000 14.500 1.3897 0.05043 0.04303 -0.0335 0.1783 1.0000 14.750 1.3943 0.05252 0.04517 -0.0329 0.1731 1.0000 15.000 1.3953 0.05498 0.04765 -0.0324 0.1681 1.0000 15.250 1.3995 0.05719 0.04993 -0.0321 0.1630 1.0000 15.500 1.4010 0.05973 0.05252 -0.0318 0.1573 1.0000 15.750 1.4005 0.06249 0.05530 -0.0315 0.1522 1.0000 16.000 1.4023 0.06508 0.05797 -0.0314 0.1460 1.0000 16.250 1.3982 0.06837 0.06126 -0.0314 0.1402 1.0000 16.500 1.3996 0.07110 0.06409 -0.0314 0.1335 1.0000 16.750 1.3952 0.07455 0.06757 -0.0316 0.1271 1.0000 17.000 1.3928 0.07782 0.07091 -0.0318 0.1200 1.0000 17.250 1.3877 0.08146 0.07459 -0.0322 0.1134 1.0000 17.500 1.3808 0.08542 0.07857 -0.0328 0.1070 1.0000 17.750 1.3744 0.08936 0.08256 -0.0334 0.1018 1.0000 18.000 1.3664 0.09357 0.08680 -0.0343 0.0975 1.0000 18.250 1.3597 0.09766 0.09093 -0.0351 0.0941 1.0000