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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.6577 0.11173 0.10816 -0.0792 0.9997 0.0371 -18.500 -0.6843 0.10222 0.09843 -0.0864 0.9989 0.0369 -18.250 -0.6993 0.09481 0.09085 -0.0924 0.9978 0.0368 -18.000 -0.7081 0.08856 0.08445 -0.0978 0.9964 0.0367 -17.750 -0.7130 0.08297 0.07872 -0.1028 0.9949 0.0367 -17.500 -0.7138 0.07804 0.07366 -0.1076 0.9934 0.0367 -17.250 -0.7090 0.07398 0.06949 -0.1118 0.9921 0.0367 -17.000 -0.7054 0.07023 0.06564 -0.1151 0.9901 0.0367 -16.750 -0.6995 0.06691 0.06224 -0.1181 0.9877 0.0367 -16.500 -0.6925 0.06359 0.05882 -0.1213 0.9855 0.0368 -16.250 -0.6818 0.06065 0.05581 -0.1245 0.9835 0.0368 -16.000 -0.6688 0.05789 0.05297 -0.1278 0.9818 0.0369 -15.750 -0.6541 0.05530 0.05030 -0.1310 0.9803 0.0369 -15.500 -0.6385 0.05271 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0.5339 0.3197 -1.250 0.3715 0.01125 0.00415 -0.1070 0.5276 0.3278 -1.000 0.3946 0.01135 0.00420 -0.1059 0.5220 0.3346 -0.750 0.4159 0.01136 0.00425 -0.1046 0.5162 0.3424 -0.500 0.4377 0.01145 0.00431 -0.1033 0.5106 0.3510 -0.250 0.4612 0.01160 0.00440 -0.1025 0.5054 0.3596 0.000 0.4844 0.01164 0.00449 -0.1015 0.5015 0.3691 0.250 0.5067 0.01172 0.00457 -0.1004 0.4972 0.3782 0.500 0.5284 0.01177 0.00465 -0.0991 0.4927 0.3876 0.750 0.5507 0.01188 0.00474 -0.0981 0.4883 0.3966 1.000 0.5751 0.01204 0.00484 -0.0974 0.4829 0.4053 1.250 0.5957 0.01206 0.00494 -0.0960 0.4796 0.4161 1.500 0.6167 0.01213 0.00504 -0.0946 0.4753 0.4273 1.750 0.6375 0.01220 0.00515 -0.0933 0.4711 0.4405 2.000 0.6587 0.01232 0.00526 -0.0920 0.4667 0.4542 2.250 0.6828 0.01247 0.00540 -0.0914 0.4625 0.4705 2.500 0.7034 0.01251 0.00554 -0.0900 0.4597 0.4884 2.750 0.7243 0.01258 0.00568 -0.0887 0.4563 0.5065 3.000 0.7451 0.01267 0.00583 -0.0874 0.4529 0.5261 3.250 0.7658 0.01279 0.00597 -0.0861 0.4493 0.5462 3.500 0.7867 0.01293 0.00614 -0.0849 0.4456 0.5663 3.750 0.8089 0.01306 0.00631 -0.0839 0.4420 0.5874 4.000 0.8280 0.01314 0.00650 -0.0823 0.4389 0.6081 4.250 0.8468 0.01324 0.00668 -0.0807 0.4352 0.6301 4.500 0.8650 0.01335 0.00686 -0.0791 0.4312 0.6547 4.750 0.8834 0.01348 0.00706 -0.0774 0.4275 0.6837 5.000 0.9025 0.01361 0.00727 -0.0759 0.4234 0.7214 5.250 0.9163 0.01362 0.00754 -0.0733 0.4203 0.7828 5.500 0.9738 0.01359 0.00791 -0.0797 0.4153 0.9239 5.750 1.0276 0.01395 0.00823 -0.0856 0.4100 1.0000 6.000 1.0465 0.01427 0.00847 -0.0844 0.4056 1.0000 6.250 1.0669 0.01452 0.00874 -0.0833 0.4018 1.0000 6.500 1.0869 0.01479 0.00901 -0.0823 0.3973 1.0000 6.750 1.1054 0.01512 0.00931 -0.0810 0.3925 1.0000 7.000 1.1227 0.01552 0.00965 -0.0796 0.3875 1.0000 7.250 1.1425 0.01585 0.00999 -0.0786 0.3829 1.0000 7.500 1.1612 0.01621 0.01036 -0.0775 0.3774 1.0000 7.750 1.1779 0.01668 0.01079 -0.0762 0.3716 1.0000 8.000 1.1952 0.01715 0.01123 -0.0750 0.3659 1.0000 8.250 1.2131 0.01760 0.01170 -0.0739 0.3593 1.0000 8.500 1.2276 0.01822 0.01227 -0.0724 0.3524 1.0000 8.750 1.2447 0.01876 0.01281 -0.0713 0.3450 1.0000 9.000 1.2583 0.01949 0.01350 -0.0699 0.3366 1.0000 9.250 1.2731 0.02019 0.01419 -0.0686 0.3281 1.0000 9.500 1.2838 0.02112 0.01507 -0.0670 0.3183 1.0000 9.750 1.2973 0.02196 0.01589 -0.0658 0.3087 1.0000 10.000 1.3054 0.02313 0.01699 -0.0640 0.2987 1.0000 10.250 1.3176 0.02411 0.01795 -0.0628 0.2898 1.0000 10.500 1.3257 0.02536 0.01916 -0.0612 0.2818 1.0000 10.750 1.3376 0.02643 0.02021 -0.0601 0.2750 1.0000 11.000 1.3450 0.02780 0.02153 -0.0586 0.2692 1.0000 11.250 1.3576 0.02887 0.02261 -0.0577 0.2645 1.0000 11.500 1.3692 0.03002 0.02378 -0.0567 0.2603 1.0000 11.750 1.3787 0.03133 0.02507 -0.0555 0.2565 1.0000 12.000 1.3861 0.03280 0.02650 -0.0543 0.2528 1.0000 12.250 1.3995 0.03389 0.02764 -0.0536 0.2503 1.0000 12.500 1.4129 0.03498 0.02877 -0.0530 0.2479 1.0000 12.750 1.4239 0.03626 0.03007 -0.0522 0.2454 1.0000 13.000 1.4343 0.03759 0.03142 -0.0513 0.2431 1.0000 13.250 1.4441 0.03897 0.03279 -0.0505 0.2409 1.0000 13.500 1.4532 0.04040 0.03421 -0.0497 0.2387 1.0000 13.750 1.4650 0.04161 0.03544 -0.0490 0.2366 1.0000 14.000 1.4774 0.04286 0.03676 -0.0485 0.2352 1.0000 14.250 1.4885 0.04422 0.03818 -0.0479 0.2337 1.0000 14.500 1.4997 0.04557 0.03957 -0.0474 0.2321 1.0000 14.750 1.5107 0.04693 0.04097 -0.0469 0.2305 1.0000 15.000 1.5207 0.04841 0.04248 -0.0464 0.2289 1.0000 15.250 1.5311 0.04982 0.04392 -0.0459 0.2275 1.0000 15.500 1.5419 0.05117 0.04528 -0.0454 0.2259 1.0000 15.750 1.5536 0.05238 0.04649 -0.0449 0.2242 1.0000 16.000 1.5699 0.05307 0.04715 -0.0444 0.2224 1.0000 16.250 1.5780 0.05481 0.04898 -0.0441 0.2214 1.0000 16.500 1.5867 0.05648 0.05074 -0.0438 0.2203 1.0000 16.750 1.5958 0.05810 0.05242 -0.0435 0.2192 1.0000 17.000 1.6046 0.05974 0.05413 -0.0432 0.2180 1.0000 17.250 1.6142 0.06130 0.05574 -0.0430 0.2168 1.0000 17.500 1.6222 0.06302 0.05752 -0.0427 0.2154 1.0000 17.750 1.6304 0.06471 0.05926 -0.0425 0.2140 1.0000 18.000 1.6391 0.06635 0.06093 -0.0423 0.2126 1.0000 18.250 1.6487 0.06783 0.06242 -0.0421 0.2108 1.0000 18.500 1.6641 0.06858 0.06315 -0.0418 0.2090 1.0000 18.750 1.6731 0.07013 0.06476 -0.0416 0.2074 1.0000 19.000 1.6718 0.07302 0.06777 -0.0417 0.2060 1.0000 19.250 1.6692 0.07607 0.07093 -0.0418 0.2041 1.0000