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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.6162 0.11869 0.11459 -0.0845 0.9974 0.0274 -19.500 -0.6185 0.11336 0.10916 -0.0887 0.9963 0.0275 -19.250 -0.6174 0.10866 0.10437 -0.0925 0.9949 0.0275 -19.000 -0.6156 0.10415 0.09978 -0.0962 0.9932 0.0276 -18.750 -0.6140 0.09985 0.09539 -0.0996 0.9912 0.0277 -18.500 -0.6108 0.09614 0.09162 -0.1022 0.9894 0.0277 -18.250 -0.6066 0.09256 0.08798 -0.1050 0.9875 0.0278 -18.000 -0.6035 0.08872 0.08406 -0.1080 0.9855 0.0279 -17.750 -0.5972 0.08534 0.08061 -0.1109 0.9836 0.0280 -17.500 -0.5941 0.08141 0.07659 -0.1143 0.9818 0.0281 -17.250 -0.5869 0.07809 0.07321 -0.1173 0.9803 0.0282 -17.000 -0.5779 0.07496 0.07002 -0.1203 0.9788 0.0283 -16.750 -0.5690 0.07214 0.06715 -0.1228 0.9768 0.0283 -16.500 -0.5624 0.06957 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2.750 0.6840 0.01317 0.00561 -0.0817 0.4149 0.4041 3.250 0.7277 0.01339 0.00592 -0.0796 0.4086 0.4312 3.500 0.7486 0.01352 0.00609 -0.0784 0.4044 0.4467 3.750 0.7684 0.01369 0.00629 -0.0771 0.4005 0.4629 4.000 0.7862 0.01390 0.00652 -0.0754 0.3959 0.4812 4.250 0.8067 0.01406 0.00673 -0.0743 0.3923 0.4956 4.500 0.8279 0.01422 0.00693 -0.0732 0.3882 0.5107 4.750 0.8473 0.01441 0.00717 -0.0719 0.3838 0.5263 5.000 0.8650 0.01466 0.00744 -0.0703 0.3793 0.5421 5.250 0.8830 0.01492 0.00772 -0.0688 0.3753 0.5602 5.500 0.9033 0.01510 0.00798 -0.0677 0.3710 0.5780 5.750 0.9218 0.01534 0.00827 -0.0663 0.3660 0.5961 6.000 0.9376 0.01567 0.00863 -0.0646 0.3607 0.6154 6.250 0.9549 0.01595 0.00896 -0.0631 0.3561 0.6380 6.500 0.9727 0.01620 0.00930 -0.0616 0.3503 0.6647 6.750 0.9867 0.01654 0.00974 -0.0596 0.3441 0.6994 7.250 1.0940 0.01722 0.01098 -0.0721 0.3258 0.9507 7.500 1.1155 0.01781 0.01154 -0.0717 0.3184 1.0000 7.750 1.1309 0.01845 0.01212 -0.0704 0.3097 1.0000 8.000 1.1469 0.01908 0.01272 -0.0692 0.3013 1.0000 8.250 1.1604 0.01987 0.01345 -0.0678 0.2922 1.0000 8.500 1.1756 0.02059 0.01414 -0.0666 0.2833 1.0000 8.750 1.1878 0.02150 0.01500 -0.0652 0.2750 1.0000 9.000 1.2021 0.02234 0.01579 -0.0640 0.2666 1.0000 9.250 1.2130 0.02339 0.01680 -0.0626 0.2593 1.0000 9.500 1.2283 0.02420 0.01761 -0.0616 0.2540 1.0000 9.750 1.2408 0.02522 0.01860 -0.0605 0.2484 1.0000 10.000 1.2523 0.02632 0.01968 -0.0593 0.2439 1.0000 10.250 1.2671 0.02723 0.02061 -0.0585 0.2399 1.0000 10.500 1.2805 0.02826 0.02164 -0.0576 0.2365 1.0000 10.750 1.2918 0.02944 0.02282 -0.0566 0.2325 1.0000 11.000 1.3016 0.03077 0.02413 -0.0555 0.2292 1.0000 11.250 1.3151 0.03184 0.02523 -0.0548 0.2269 1.0000 11.500 1.3282 0.03297 0.02638 -0.0540 0.2243 1.0000 11.750 1.3410 0.03413 0.02757 -0.0533 0.2226 1.0000 12.000 1.3524 0.03542 0.02888 -0.0526 0.2203 1.0000 12.250 1.3618 0.03688 0.03036 -0.0518 0.2181 1.0000 12.500 1.3717 0.03831 0.03181 -0.0510 0.2162 1.0000 12.750 1.3796 0.03994 0.03346 -0.0502 0.2143 1.0000 13.000 1.3889 0.04146 0.03500 -0.0495 0.2127 1.0000 13.250 1.4007 0.04281 0.03641 -0.0490 0.2117 1.0000 13.500 1.4123 0.04419 0.03783 -0.0485 0.2108 1.0000 13.750 1.4234 0.04560 0.03929 -0.0480 0.2096 1.0000 14.000 1.4330 0.04717 0.04091 -0.0476 0.2085 1.0000 14.250 1.4427 0.04874 0.04252 -0.0471 0.2070 1.0000 14.500 1.4512 0.05044 0.04427 -0.0466 0.2058 1.0000 14.750 1.4589 0.05222 0.04609 -0.0462 0.2043 1.0000 15.000 1.4661 0.05408 0.04798 -0.0458 0.2029 1.0000 15.250 1.4722 0.05603 0.04996 -0.0454 0.2015 1.0000 15.500 1.4784 0.05798 0.05194 -0.0450 0.2001 1.0000 15.750 1.4838 0.06002 0.05402 -0.0446 0.1987 1.0000 16.000 1.4921 0.06177 0.05581 -0.0444 0.1976 1.0000 16.250 1.5009 0.06352 0.05763 -0.0442 0.1969 1.0000 16.500 1.5093 0.06533 0.05950 -0.0440 0.1959 1.0000 16.750 1.5181 0.06708 0.06131 -0.0439 0.1949 1.0000 17.000 1.5250 0.06903 0.06333 -0.0438 0.1938 1.0000 17.250 1.5315 0.07103 0.06539 -0.0437 0.1924 1.0000 17.500 1.5390 0.07290 0.06732 -0.0436 0.1913 1.0000 17.750 1.5448 0.07498 0.06945 -0.0436 0.1902 1.0000 18.000 1.5500 0.07712 0.07163 -0.0435 0.1888 1.0000 18.250 1.5558 0.07918 0.07373 -0.0435 0.1876 1.0000 18.500 1.5591 0.08151 0.07609 -0.0435 0.1860 1.0000 18.750 1.5631 0.08373 0.07832 -0.0435 0.1842 1.0000 19.000 1.5690 0.08583 0.08051 -0.0437 0.1830 1.0000 19.250 1.5727 0.08822 0.08299 -0.0439 0.1812 1.0000