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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.6127 0.10641 0.10292 -0.0984 0.9898 0.0241 -19.250 -0.6075 0.10320 0.09967 -0.1007 0.9882 0.0241 -19.000 -0.6031 0.09981 0.09624 -0.1031 0.9865 0.0242 -18.750 -0.5997 0.09620 0.09258 -0.1058 0.9849 0.0243 -18.500 -0.5924 0.09325 0.08960 -0.1081 0.9832 0.0243 -18.250 -0.5875 0.08976 0.08607 -0.1108 0.9816 0.0244 -18.000 -0.5814 0.08639 0.08266 -0.1136 0.9801 0.0245 -17.750 -0.5749 0.08311 0.07933 -0.1164 0.9788 0.0246 -17.500 -0.5702 0.07987 0.07605 -0.1188 0.9766 0.0246 -17.250 -0.5667 0.07693 0.07307 -0.1204 0.9727 0.0247 -17.000 -0.5617 0.07375 0.06985 -0.1229 0.9696 0.0247 -16.750 -0.5527 0.07077 0.06683 -0.1257 0.9666 0.0247 -16.500 -0.5436 0.06751 0.06352 -0.1290 0.9640 0.0248 -16.250 -0.5359 0.06438 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0.4535 0.1163 -1.500 0.3348 0.01041 0.00319 -0.1046 0.4509 0.1298 -1.250 0.3577 0.01037 0.00319 -0.1036 0.4472 0.1416 -1.000 0.3803 0.01037 0.00321 -0.1025 0.4435 0.1513 -0.750 0.4020 0.01039 0.00324 -0.1012 0.4388 0.1595 -0.500 0.4235 0.01043 0.00328 -0.1000 0.4345 0.1687 -0.250 0.4457 0.01037 0.00329 -0.0989 0.4314 0.1899 0.000 0.4668 0.01023 0.00333 -0.0976 0.4283 0.2415 0.250 0.4892 0.01023 0.00340 -0.0966 0.4251 0.2618 0.500 0.5113 0.01028 0.00348 -0.0954 0.4213 0.2770 0.750 0.5326 0.01037 0.00357 -0.0941 0.4167 0.2863 1.000 0.5546 0.01045 0.00366 -0.0930 0.4127 0.2946 1.250 0.5778 0.01053 0.00374 -0.0921 0.4087 0.3001 1.500 0.5995 0.01061 0.00383 -0.0909 0.4039 0.3089 1.750 0.6203 0.01072 0.00395 -0.0895 0.3989 0.3186 2.000 0.6415 0.01086 0.00407 -0.0883 0.3951 0.3243 2.250 0.6642 0.01093 0.00417 -0.0874 0.3918 0.3332 2.500 0.6864 0.01103 0.00428 -0.0863 0.3878 0.3383 2.750 0.7077 0.01116 0.00441 -0.0851 0.3839 0.3452 3.000 0.7277 0.01130 0.00457 -0.0837 0.3795 0.3558 3.250 0.7483 0.01145 0.00472 -0.0825 0.3756 0.3656 3.500 0.7704 0.01155 0.00486 -0.0815 0.3722 0.3770 3.750 0.7917 0.01169 0.00502 -0.0803 0.3680 0.3877 4.000 0.8110 0.01187 0.00522 -0.0789 0.3632 0.3992 4.250 0.8296 0.01208 0.00543 -0.0774 0.3582 0.4148 4.500 0.8507 0.01221 0.00562 -0.0763 0.3542 0.4322 4.750 0.8707 0.01238 0.00583 -0.0750 0.3489 0.4503 5.000 0.8883 0.01264 0.00610 -0.0734 0.3429 0.4678 5.250 0.9074 0.01286 0.00635 -0.0720 0.3380 0.4827 5.500 0.9262 0.01310 0.00661 -0.0706 0.3315 0.4960 5.750 0.9431 0.01343 0.00692 -0.0690 0.3244 0.5094 6.000 0.9614 0.01369 0.00721 -0.0676 0.3176 0.5243 6.250 0.9767 0.01408 0.00759 -0.0657 0.3093 0.5382 6.500 0.9930 0.01443 0.00796 -0.0641 0.3003 0.5567 6.750 1.0073 0.01487 0.00839 -0.0622 0.2905 0.5718 7.000 1.0215 0.01532 0.00884 -0.0603 0.2810 0.5882 7.250 1.0347 0.01583 0.00935 -0.0583 0.2712 0.6071 7.500 1.0483 0.01633 0.00986 -0.0565 0.2624 0.6276 7.750 1.0608 0.01687 0.01043 -0.0545 0.2539 0.6524 8.000 1.0721 0.01746 0.01106 -0.0524 0.2453 0.6831 8.250 1.0866 0.01786 0.01160 -0.0507 0.2407 0.7308 8.500 1.2169 0.01871 0.01291 -0.0733 0.2270 0.9962 8.750 1.2422 0.01931 0.01350 -0.0737 0.2245 1.0000 9.000 1.2599 0.01992 0.01411 -0.0728 0.2216 1.0000 9.250 1.2757 0.02064 0.01482 -0.0718 0.2181 1.0000 9.500 1.2923 0.02134 0.01551 -0.0709 0.2154 1.0000 9.750 1.3081 0.02210 0.01626 -0.0699 0.2123 1.0000 10.000 1.3254 0.02279 0.01697 -0.0691 0.2104 1.0000 10.250 1.3428 0.02348 0.01767 -0.0684 0.2088 1.0000 10.500 1.3593 0.02424 0.01844 -0.0676 0.2071 1.0000 10.750 1.3744 0.02510 0.01930 -0.0667 0.2054 1.0000 11.000 1.3901 0.02593 0.02015 -0.0659 0.2040 1.0000 11.250 1.4040 0.02689 0.02113 -0.0650 0.2024 1.0000 11.500 1.4175 0.02791 0.02215 -0.0642 0.2007 1.0000 11.750 1.4318 0.02888 0.02314 -0.0634 0.1994 1.0000 12.000 1.4437 0.03004 0.02433 -0.0625 0.1979 1.0000 12.250 1.4592 0.03095 0.02527 -0.0618 0.1974 1.0000 12.500 1.4738 0.03194 0.02629 -0.0612 0.1967 1.0000 12.750 1.4874 0.03303 0.02742 -0.0605 0.1960 1.0000 13.000 1.5014 0.03408 0.02851 -0.0599 0.1952 1.0000 13.250 1.5134 0.03531 0.02977 -0.0592 0.1936 1.0000 13.500 1.5255 0.03654 0.03104 -0.0585 0.1928 1.0000 13.750 1.5370 0.03783 0.03235 -0.0579 0.1915 1.0000 14.000 1.5460 0.03935 0.03391 -0.0571 0.1902 1.0000 14.250 1.5557 0.04081 0.03540 -0.0564 0.1889 1.0000 14.500 1.5633 0.04250 0.03713 -0.0557 0.1879 1.0000 14.750 1.5714 0.04414 0.03881 -0.0551 0.1867 1.0000 15.000 1.5768 0.04608 0.04078 -0.0544 0.1854 1.0000 15.250 1.5831 0.04792 0.04266 -0.0538 0.1842 1.0000 15.500 1.5903 0.04971 0.04450 -0.0532 0.1836 1.0000 15.750 1.6002 0.05127 0.04611 -0.0529 0.1831 1.0000 16.000 1.6089 0.05296 0.04786 -0.0525 0.1825 1.0000 16.250 1.6168 0.05474 0.04970 -0.0521 0.1817 1.0000 16.500 1.6251 0.05647 0.05148 -0.0518 0.1806 1.0000 16.750 1.6304 0.05853 0.05359 -0.0515 0.1793 1.0000 17.000 1.6365 0.06049 0.05560 -0.0512 0.1776 1.0000 17.250 1.6391 0.06286 0.05801 -0.0509 0.1762 1.0000 17.500 1.6434 0.06503 0.06022 -0.0506 0.1749 1.0000 17.750 1.6424 0.06783 0.06306 -0.0503 0.1730 1.0000 18.000 1.6422 0.07049 0.06576 -0.0501 0.1711 1.0000 18.250 1.6470 0.07266 0.06800 -0.0500 0.1697 1.0000 18.500 1.6530 0.07468 0.07006 -0.0499 0.1679 1.0000 18.750 1.6549 0.07718 0.07261 -0.0499 0.1648 1.0000 19.000 1.6548 0.07992 0.07538 -0.0498 0.1623 1.0000