XFOIL Version 6.96 Calculated polar for: GOE 502 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.5864 0.08223 0.07970 -0.0980 0.9940 0.0325 -15.250 -0.6242 0.07060 0.06786 -0.1085 0.9921 0.0327 -15.000 -0.6385 0.06361 0.06076 -0.1151 0.9890 0.0328 -14.750 -0.6414 0.05835 0.05541 -0.1210 0.9863 0.0330 -14.500 -0.6479 0.05235 0.04928 -0.1283 0.9836 0.0330 -14.250 -0.6423 0.04788 0.04473 -0.1346 0.9817 0.0332 -14.000 -0.6438 0.04364 0.04040 -0.1392 0.9757 0.0333 -13.750 -0.6361 0.03967 0.03635 -0.1449 0.9716 0.0335 -13.500 -0.6236 0.03569 0.03226 -0.1516 0.9686 0.0337 -13.250 -0.6140 0.03228 0.02876 -0.1566 0.9607 0.0339 -13.000 -0.5898 0.02858 0.02492 -0.1650 0.9563 0.0341 -12.750 -0.5604 0.02501 0.02119 -0.1750 0.9505 0.0344 -12.500 -0.5353 0.02334 0.01940 -0.1786 0.9441 0.0347 -12.250 -0.5060 0.02206 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0.00835 0.00228 -0.1660 0.6541 0.0986 -2.250 0.4717 0.00817 0.00220 -0.1656 0.6472 0.1300 -2.000 0.4972 0.00811 0.00215 -0.1650 0.6400 0.1486 -1.750 0.5244 0.00801 0.00212 -0.1647 0.6331 0.1652 -1.500 0.5500 0.00798 0.00209 -0.1641 0.6243 0.1797 -1.250 0.5762 0.00795 0.00208 -0.1636 0.6159 0.1933 -1.000 0.6017 0.00795 0.00208 -0.1629 0.6059 0.2063 -0.750 0.6273 0.00796 0.00209 -0.1623 0.5959 0.2185 -0.250 0.6773 0.00804 0.00213 -0.1608 0.5748 0.2414 0.000 0.7014 0.00811 0.00218 -0.1599 0.5649 0.2518 0.250 0.7270 0.00817 0.00222 -0.1593 0.5560 0.2606 0.500 0.7507 0.00826 0.00229 -0.1583 0.5470 0.2712 0.750 0.7767 0.00831 0.00234 -0.1577 0.5400 0.2808 1.000 0.8011 0.00839 0.00241 -0.1569 0.5329 0.2900 1.250 0.8258 0.00848 0.00247 -0.1561 0.5265 0.2964 1.500 0.8512 0.00852 0.00254 -0.1555 0.5207 0.3066 1.750 0.8752 0.00862 0.00262 -0.1546 0.5144 0.3159 2.000 0.8989 0.00870 0.00271 -0.1536 0.5089 0.3267 2.250 0.9239 0.00874 0.00278 -0.1529 0.5045 0.3363 2.500 0.9472 0.00880 0.00285 -0.1519 0.4993 0.3473 2.750 0.9686 0.00892 0.00295 -0.1504 0.4932 0.3586 3.000 0.9923 0.00896 0.00305 -0.1495 0.4879 0.3747 3.250 1.0157 0.00901 0.00314 -0.1485 0.4822 0.3907 3.500 1.0375 0.00913 0.00326 -0.1472 0.4766 0.4075 3.750 1.0596 0.00924 0.00340 -0.1459 0.4716 0.4257 4.000 1.0839 0.00929 0.00351 -0.1451 0.4673 0.4458 4.250 1.1063 0.00939 0.00364 -0.1440 0.4618 0.4658 4.500 1.1266 0.00955 0.00381 -0.1424 0.4555 0.4854 4.750 1.1501 0.00961 0.00394 -0.1415 0.4514 0.5094 5.000 1.1732 0.00966 0.00409 -0.1405 0.4470 0.5427 5.250 1.1935 0.00967 0.00430 -0.1390 0.4419 0.6273 5.500 1.2242 0.00932 0.00461 -0.1398 0.4355 1.0000 5.750 1.2480 0.00944 0.00473 -0.1390 0.4305 1.0000 6.000 1.2698 0.00961 0.00489 -0.1378 0.4247 1.0000 6.250 1.2897 0.00985 0.00508 -0.1363 0.4189 1.0000 6.500 1.3126 0.01000 0.00524 -0.1353 0.4141 1.0000 6.750 1.3340 0.01020 0.00543 -0.1341 0.4078 1.0000 7.000 1.3519 0.01050 0.00567 -0.1323 0.4000 1.0000 7.250 1.3743 0.01068 0.00586 -0.1313 0.3934 1.0000 7.500 1.3928 0.01097 0.00612 -0.1297 0.3855 1.0000 7.750 1.4127 0.01123 0.00636 -0.1283 0.3789 1.0000 8.000 1.4318 0.01153 0.00663 -0.1268 0.3707 1.0000 8.250 1.4496 0.01187 0.00695 -0.1251 0.3632 1.0000 8.500 1.4689 0.01217 0.00725 -0.1237 0.3556 1.0000 8.750 1.4851 0.01260 0.00763 -0.1219 0.3472 1.0000 9.000 1.5026 0.01298 0.00800 -0.1203 0.3368 1.0000 9.250 1.5180 0.01347 0.00844 -0.1184 0.3264 1.0000 9.500 1.5319 0.01403 0.00895 -0.1163 0.3150 1.0000 9.750 1.5467 0.01457 0.00946 -0.1144 0.3026 1.0000 10.000 1.5600 0.01520 0.01004 -0.1124 0.2899 1.0000 10.250 1.5701 0.01600 0.01077 -0.1100 0.2739 1.0000 10.500 1.5780 0.01695 0.01162 -0.1073 0.2547 1.0000 10.750 1.5831 0.01808 0.01264 -0.1045 0.2344 1.0000 11.000 1.5865 0.01936 0.01381 -0.1016 0.2131 1.0000 11.250 1.5879 0.02082 0.01515 -0.0986 0.1919 1.0000 11.500 1.5941 0.02207 0.01634 -0.0963 0.1796 1.0000 11.750 1.6002 0.02337 0.01761 -0.0941 0.1700 1.0000 12.000 1.6084 0.02459 0.01881 -0.0922 0.1627 1.0000 12.250 1.6168 0.02586 0.02008 -0.0905 0.1566 1.0000 12.500 1.6268 0.02705 0.02129 -0.0890 0.1519 1.0000 12.750 1.6335 0.02852 0.02275 -0.0874 0.1463 1.0000 13.000 1.6435 0.02980 0.02406 -0.0861 0.1426 1.0000 13.250 1.6533 0.03113 0.02541 -0.0848 0.1387 1.0000 13.500 1.6604 0.03271 0.02700 -0.0835 0.1343 1.0000 13.750 1.6674 0.03432 0.02864 -0.0822 0.1301 1.0000 14.000 1.6766 0.03578 0.03013 -0.0811 0.1263 1.0000 14.250 1.6820 0.03759 0.03194 -0.0799 0.1219 1.0000 14.500 1.6872 0.03946 0.03383 -0.0788 0.1173 1.0000 14.750 1.6938 0.04120 0.03560 -0.0777 0.1130 1.0000 15.000 1.6943 0.04353 0.03793 -0.0764 0.1074 1.0000 15.250 1.6981 0.04559 0.04001 -0.0754 0.1018 1.0000 15.500 1.6977 0.04808 0.04249 -0.0743 0.0956 1.0000 15.750 1.6937 0.05099 0.04538 -0.0731 0.0879 1.0000 16.000 1.6907 0.05384 0.04824 -0.0721 0.0811 1.0000 16.250 1.6853 0.05701 0.05141 -0.0712 0.0744 1.0000 16.500 1.6805 0.06019 0.05460 -0.0704 0.0696 1.0000 16.750 1.6755 0.06345 0.05788 -0.0697 0.0655 1.0000 17.000 1.6712 0.06670 0.06117 -0.0692 0.0627 1.0000 17.250 1.6679 0.06991 0.06442 -0.0688 0.0601 1.0000 17.500 1.6637 0.07326 0.06780 -0.0684 0.0581 1.0000 17.750 1.6599 0.07665 0.07125 -0.0683 0.0564 1.0000 18.000 1.6586 0.07974 0.07440 -0.0682 0.0549 1.0000 18.250 1.6571 0.08289 0.07761 -0.0681 0.0538 1.0000 18.500 1.6522 0.08656 0.08133 -0.0683 0.0524 1.0000 18.750 1.6474 0.09024 0.08506 -0.0685 0.0511 1.0000