XFOIL Version 6.96 Calculated polar for: GOE 570 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.0477 0.06231 0.05682 -0.2232 0.6877 0.0446 -19.500 -0.0515 0.05971 0.05418 -0.2242 0.6846 0.0451 -19.250 -0.0510 0.05765 0.05206 -0.2248 0.6817 0.0450 -19.000 -0.0535 0.05543 0.04976 -0.2254 0.6781 0.0448 -18.750 -0.0561 0.05306 0.04736 -0.2261 0.6757 0.0452 -18.500 -0.0553 0.05100 0.04528 -0.2267 0.6741 0.0455 -18.250 -0.0569 0.04887 0.04310 -0.2272 0.6714 0.0456 -18.000 -0.0588 0.04681 0.04100 -0.2275 0.6685 0.0456 -17.750 -0.0599 0.04490 0.03903 -0.2276 0.6646 0.0457 -17.500 -0.0586 0.04319 0.03728 -0.2277 0.6615 0.0461 -17.250 -0.0593 0.04149 0.03552 -0.2274 0.6583 0.0462 -17.000 -0.0584 0.03986 0.03384 -0.2272 0.6554 0.0464 -16.750 -0.0582 0.03820 0.03215 -0.2270 0.6532 0.0464 -16.500 -0.0581 0.03659 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0.2038 2.750 0.3688 0.03032 0.02298 -0.0169 0.3983 0.2071 3.000 0.3808 0.03112 0.02377 -0.0159 0.3950 0.2104 3.250 0.3968 0.03173 0.02438 -0.0153 0.3931 0.2137 3.500 0.4162 0.03220 0.02487 -0.0152 0.3917 0.2149 3.750 0.4337 0.03280 0.02547 -0.0148 0.3898 0.2168 4.000 0.4493 0.03349 0.02619 -0.0143 0.3877 0.2228 4.250 0.4663 0.03410 0.02682 -0.0140 0.3859 0.2268 4.500 0.4824 0.03477 0.02751 -0.0136 0.3837 0.2329 5.000 0.5079 0.03649 0.02929 -0.0122 0.3786 0.2533 5.250 0.5236 0.03711 0.03040 -0.0124 0.3762 0.3914 5.500 0.5422 0.03762 0.03107 -0.0124 0.3751 0.4329 5.750 0.5596 0.03825 0.03176 -0.0123 0.3731 0.4480 6.000 0.5766 0.03890 0.03245 -0.0121 0.3714 0.4603 6.250 0.5920 0.03964 0.03324 -0.0118 0.3694 0.4765 6.500 0.6027 0.04066 0.03434 -0.0110 0.3672 0.4952 6.750 0.6150 0.04161 0.03531 -0.0104 0.3651 0.5068 7.000 0.6271 0.04256 0.03630 -0.0098 0.3627 0.5211 7.250 0.6387 0.04352 0.03733 -0.0092 0.3603 0.5429 7.500 0.6516 0.04441 0.03833 -0.0087 0.3589 0.5690 7.750 0.6661 0.04520 0.03921 -0.0084 0.3578 0.5933 8.000 0.6777 0.04576 0.04010 -0.0074 0.3561 0.6759 8.500 0.8220 0.05016 0.04548 -0.0320 0.3520 0.9568 8.750 0.8348 0.05142 0.04673 -0.0318 0.3495 0.9609 9.000 0.8390 0.05308 0.04838 -0.0307 0.3469 0.9641 9.250 0.8444 0.05447 0.04976 -0.0294 0.3445 0.9662 9.500 0.8505 0.05535 0.05064 -0.0275 0.3431 0.9693 9.750 0.8461 0.05596 0.05127 -0.0231 0.3420 0.9717 10.000 0.8679 0.05740 0.05272 -0.0251 0.3404 0.9725 10.250 0.8835 0.05885 0.05418 -0.0260 0.3385 0.9730 10.500 0.9030 0.06019 0.05553 -0.0275 0.3367 0.9737 10.750 0.9191 0.06152 0.05685 -0.0284 0.3348 0.9743 11.000 0.9431 0.06334 0.05868 -0.0314 0.3327 0.9758 11.250 0.9469 0.06538 0.06071 -0.0309 0.3303 0.9763 11.500 0.9640 0.06708 0.06241 -0.0325 0.3279 0.9774 11.750 0.9834 0.06831 0.06366 -0.0339 0.3271 0.9784 12.000 1.0061 0.06974 0.06511 -0.0361 0.3260 0.9800 12.250 1.0215 0.07143 0.06682 -0.0374 0.3242 0.9812 12.500 1.0330 0.07328 0.06871 -0.0381 0.3221 0.9824 12.750 1.0523 0.07496 0.07040 -0.0401 0.3206 0.9843 13.000 1.0652 0.07660 0.07204 -0.0408 0.3188 0.9856 13.250 1.0737 0.07870 0.07414 -0.0411 0.3163 0.9875 13.500 1.0714 0.08096 0.07640 -0.0398 0.3137 0.9882 13.750 1.0797 0.08218 0.07764 -0.0393 0.3124 0.9884 14.000 1.0852 0.08340 0.07888 -0.0380 0.3113 0.9889 14.250 1.1048 0.08498 0.08049 -0.0402 0.3102 0.9896 14.500 1.1211 0.08674 0.08229 -0.0421 0.3087 0.9902 14.750 1.1117 0.08814 0.08371 -0.0385 0.3072 0.9895 15.000 1.1320 0.09006 0.08564 -0.0414 0.3054 0.9903 15.250 1.1435 0.09176 0.08735 -0.0423 0.3034 0.9907 15.500 1.1497 0.09334 0.08894 -0.0421 0.3017 0.9907 15.750 1.1492 0.09554 0.09114 -0.0414 0.2994 0.9908 16.000 1.1511 0.09709 0.09270 -0.0404 0.2970 0.9906 16.250 1.1637 0.09853 0.09418 -0.0412 0.2962 0.9909 16.500 1.1704 0.10006 0.09575 -0.0411 0.2948 0.9910 16.750 1.1740 0.10190 0.09762 -0.0409 0.2926 0.9910 17.000 1.1762 0.10386 0.09961 -0.0405 0.2912 0.9911 17.250 1.1808 0.10557 0.10133 -0.0404 0.2889 0.9911 17.500 1.1837 0.10744 0.10318 -0.0401 0.2860 0.9912 17.750 1.1906 0.10891 0.10463 -0.0402 0.2836 0.9912 18.000 1.1881 0.11136 0.10715 -0.0397 0.2819 0.9913 18.250 1.1924 0.11311 0.10894 -0.0396 0.2803 0.9913 18.500 1.1992 0.11461 0.11047 -0.0397 0.2789 0.9914 18.750 1.2068 0.11601 0.11190 -0.0399 0.2777 0.9914 19.000 1.1976 0.11911 0.11501 -0.0392 0.2731 0.9915 19.250 1.2033 0.12068 0.11657 -0.0393 0.2714 0.9915