XFOIL Version 6.94 Calculated polar for: GOE 650 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5337 0.00885 0.00289 -0.1246 0.7371 0.3733 0.500 0.5866 0.00886 0.00290 -0.1234 0.7197 0.3997 1.000 0.6369 0.00886 0.00294 -0.1217 0.7006 0.4252 1.500 0.6869 0.00888 0.00299 -0.1200 0.6787 0.4505 2.000 0.7351 0.00893 0.00305 -0.1178 0.6518 0.4772 2.500 0.7802 0.00900 0.00313 -0.1151 0.6167 0.5068 3.000 0.8206 0.00922 0.00327 -0.1115 0.5721 0.5444 3.500 0.8576 0.00954 0.00356 -0.1073 0.5285 0.6000 4.000 0.8919 0.00971 0.00391 -0.1026 0.4887 0.7045 6.000 1.0391 0.01311 0.00627 -0.0886 0.2364 1.0000 6.500 1.0737 0.01389 0.00688 -0.0847 0.2064 1.0000 7.000 1.1078 0.01473 0.00757 -0.0809 0.1806 1.0000 7.500 1.1355 0.01594 0.00849 -0.0764 0.1397 1.0000 8.000 1.1651 0.01713 0.00949 -0.0723 0.1112 1.0000 8.500 1.1917 0.01854 0.01071 -0.0681 0.0826 1.0000 9.000 1.2089 0.02061 0.01249 -0.0630 0.0373 1.0000 9.500 1.2325 0.02241 0.01425 -0.0589 0.0241 1.0000 10.000 1.2604 0.02399 0.01584 -0.0557 0.0170 1.0000 10.500 1.2812 0.02615 0.01797 -0.0520 0.0032 1.0000 11.000 1.3067 0.02805 0.01998 -0.0490 0.0027 1.0000 11.500 1.3309 0.03014 0.02218 -0.0463 0.0025 1.0000 12.000 1.3524 0.03251 0.02468 -0.0436 0.0024 1.0000 12.500 1.3713 0.03521 0.02752 -0.0411 0.0023 1.0000 13.000 1.3868 0.03831 0.03077 -0.0387 0.0023 1.0000 13.500 1.3988 0.04192 0.03455 -0.0366 0.0023 1.0000 14.000 1.4075 0.04603 0.03885 -0.0349 0.0023 1.0000 14.500 1.4119 0.05084 0.04387 -0.0335 0.0023 1.0000 15.000 1.4129 0.05634 0.04958 -0.0328 0.0023 1.0000 15.500 1.4084 0.06286 0.05633 -0.0328 0.0023 1.0000 16.000 1.4002 0.07030 0.06399 -0.0336 0.0023 1.0000 16.500 1.3853 0.07897 0.07293 -0.0352 0.0023 1.0000 17.000 1.3661 0.08868 0.08289 -0.0377 0.0023 1.0000 17.500 1.3428 0.09934 0.09381 -0.0410 0.0023 1.0000 18.000 1.3153 0.11118 0.10592 -0.0452 0.0023 1.0000 18.500 1.2887 0.12321 0.11819 -0.0501 0.0023 1.0000 19.000 1.2640 0.13529 0.13050 -0.0555 0.0023 1.0000 19.500 1.2414 0.14727 0.14269 -0.0614 0.0023 1.0000 20.000 1.2243 0.15857 0.15418 -0.0674 0.0023 1.0000 20.500 1.2076 0.17013 0.16593 -0.0739 0.0023 1.0000 21.000 1.1989 0.18010 0.17604 -0.0796 0.0023 1.0000 21.500 1.1907 0.19021 0.18630 -0.0858 0.0024 1.0000 22.000 1.1859 0.19971 0.19593 -0.0917 0.0024 1.0000 22.500 1.1826 0.20906 0.20538 -0.0977 0.0024 1.0000 23.000 1.1826 0.21766 0.21408 -0.1034 0.0024 1.0000 23.500 1.1847 0.22580 0.22231 -0.1089 0.0024 1.0000 24.000 1.1882 0.23352 0.23011 -0.1143 0.0025 1.0000 24.500 1.1935 0.24074 0.23741 -0.1196 0.0025 1.0000 25.000 1.2005 0.24746 0.24419 -0.1246 0.0025 1.0000 25.500 1.2079 0.25411 0.25091 -0.1296 0.0026 1.0000 26.000 1.2171 0.26006 0.25692 -0.1344 0.0026 1.0000 26.500 1.2249 0.26651 0.26345 -0.1395 0.0026 1.0000 27.000 1.2325 0.27304 0.27007 -0.1447 0.0027 1.0000 27.500 1.2388 0.28018 0.27731 -0.1504 0.0028 1.0000 28.000 1.2430 0.28828 0.28554 -0.1567 0.0029 1.0000 30.000 0.9417 0.41662 0.41508 -0.1855 0.0086 1.0000 30.500 0.9464 0.42381 0.42230 -0.1881 0.0084 1.0000 31.000 0.9489 0.43446 0.43296 -0.1912 0.0083 1.0000 31.500 0.9507 0.44669 0.44520 -0.1946 0.0079 1.0000 32.000 0.9534 0.45606 0.45460 -0.1975 0.0075 1.0000 32.500 0.9558 0.46510 0.46366 -0.2004 0.0071 1.0000 33.000 0.9578 0.47363 0.47222 -0.2032 0.0069 1.0000 33.500 0.9597 0.48188 0.48049 -0.2059 0.0067 1.0000 34.000 0.9611 0.48983 0.48846 -0.2086 0.0066 1.0000 34.500 0.9625 0.49734 0.49600 -0.2111 0.0065 1.0000 35.000 0.9633 0.50606 0.50474 -0.2137 0.0065 1.0000 35.500 0.9631 0.51564 0.51433 -0.2166 0.0064 1.0000 36.000 0.9628 0.52496 0.52367 -0.2194 0.0064 1.0000 36.500 0.9624 0.53345 0.53220 -0.2220 0.0064 1.0000 37.000 0.9617 0.54250 0.54127 -0.2246 0.0063 1.0000 37.500 0.9609 0.55120 0.55000 -0.2272 0.0063 1.0000 38.000 0.9596 0.55901 0.55783 -0.2297 0.0062 1.0000 38.500 0.9581 0.56704 0.56589 -0.2321 0.0061 1.0000 39.000 0.9562 0.57461 0.57349 -0.2345 0.0059 1.0000 39.500 0.9540 0.58214 0.58105 -0.2369 0.0057 1.0000 40.000 0.9515 0.58923 0.58817 -0.2393 0.0055 1.0000 40.500 0.9487 0.59597 0.59493 -0.2416 0.0052 1.0000 41.000 0.9455 0.60192 0.60091 -0.2438 0.0050 1.0000 42.000 0.9380 0.61542 0.61445 -0.2482 0.0048 1.0000 42.500 0.9346 0.62553 0.62459 -0.2503 0.0046 1.0000 43.000 0.9305 0.63242 0.63151 -0.2523 0.0041 1.0000 43.500 0.9259 0.63818 0.63730 -0.2543 0.0038 1.0000 44.000 0.9210 0.64316 0.64231 -0.2564 0.0036 1.0000 45.000 0.9104 0.65594 0.65512 -0.2602 0.0034 1.0000 45.500 0.9054 0.66357 0.66278 -0.2619 0.0032 1.0000 46.000 0.8997 0.66909 0.66833 -0.2637 0.0028 1.0000 46.500 0.8935 0.67314 0.67241 -0.2655 0.0025 1.0000 47.000 0.8869 0.67617 0.67545 -0.2673 0.0024 1.0000 48.000 0.8736 0.68696 0.68629 -0.2705 0.0023 1.0000 48.500 0.8672 0.69301 0.69236 -0.2719 0.0021 1.0000 49.000 0.8601 0.69697 0.69634 -0.2734 0.0018 1.0000 49.500 0.8526 0.69974 0.69914 -0.2748 0.0016 1.0000 50.000 0.8447 0.70129 0.70071 -0.2763 0.0015 1.0000 50.500 0.8363 0.70200 0.70144 -0.2778 0.0014 1.0000 51.500 0.8203 0.70908 0.70855 -0.2803 0.0013 1.0000 52.000 0.8122 0.71222 0.71172 -0.2814 0.0013 1.0000 52.500 0.8040 0.71469 0.71421 -0.2824 0.0012 1.0000 53.000 0.7953 0.71586 0.71540 -0.2835 0.0011 1.0000 53.500 0.7863 0.71617 0.71573 -0.2846 0.0010 1.0000 54.000 0.7771 0.71598 0.71555 -0.2856 0.0008 1.0000 54.500 0.7676 0.71510 0.71469 -0.2866 0.0007 1.0000 55.000 0.7578 0.71311 0.71272 -0.2876 0.0007 1.0000 55.500 0.7477 0.71051 0.71014 -0.2887 0.0006 1.0000 56.500 0.7287 0.71100 0.71066 -0.2900 0.0005 1.0000 57.000 0.7190 0.70960 0.70927 -0.2906 0.0005 1.0000 57.500 0.7087 0.70665 0.70635 -0.2914 0.0004 1.0000 58.000 0.6983 0.70319 0.70290 -0.2920 0.0003 1.0000 59.500 0.6666 0.69266 0.69241 -0.2936 0.0003 1.0000 60.000 0.6561 0.68891 0.68867 -0.2939 0.0002 1.0000