XFOIL Version 6.94 Calculated polar for: FX 63-120 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.8085 0.00850 0.00298 -0.1843 0.7093 0.5537 0.500 0.8651 0.00861 0.00310 -0.1842 0.6947 0.5832 1.000 0.9211 0.00875 0.00324 -0.1840 0.6787 0.6168 1.500 0.9754 0.00890 0.00336 -0.1834 0.6574 0.6490 2.000 1.0295 0.00904 0.00353 -0.1828 0.6370 0.6764 2.500 1.0832 0.00923 0.00374 -0.1821 0.6163 0.7008 3.000 1.1361 0.00946 0.00402 -0.1813 0.5936 0.7237 3.500 1.1797 0.01000 0.00424 -0.1786 0.5213 0.7465 4.000 1.2257 0.01063 0.00467 -0.1767 0.4646 0.7701 4.500 1.2614 0.01202 0.00545 -0.1731 0.3553 0.7950 5.000 1.2975 0.01338 0.00636 -0.1698 0.2611 0.8255 5.500 1.3206 0.01532 0.00771 -0.1642 0.1461 0.8847 6.500 1.3799 0.01854 0.01023 -0.1557 0.0350 1.0000 7.000 1.4031 0.02040 0.01190 -0.1505 0.0024 1.0000 7.500 1.4367 0.02155 0.01311 -0.1470 0.0018 1.0000 8.000 1.4687 0.02284 0.01449 -0.1435 0.0017 1.0000 8.500 1.4982 0.02433 0.01609 -0.1398 0.0017 1.0000 9.000 1.5247 0.02609 0.01799 -0.1360 0.0017 1.0000 9.500 1.5483 0.02816 0.02022 -0.1322 0.0018 1.0000 10.000 1.5694 0.03057 0.02280 -0.1286 0.0018 1.0000 10.500 1.5884 0.03334 0.02574 -0.1252 0.0019 1.0000 11.000 1.6050 0.03654 0.02913 -0.1221 0.0020 1.0000 11.500 1.6184 0.04027 0.03308 -0.1192 0.0021 1.0000 12.000 1.6287 0.04460 0.03764 -0.1168 0.0022 1.0000 12.500 1.6355 0.04964 0.04293 -0.1148 0.0023 1.0000 13.000 1.6374 0.05565 0.04920 -0.1134 0.0024 1.0000 13.500 1.6323 0.06308 0.05690 -0.1127 0.0025 1.0000 14.000 1.6345 0.06995 0.06400 -0.1129 0.0026 1.0000 14.500 1.6347 0.07756 0.07186 -0.1137 0.0027 1.0000 15.000 1.6286 0.08664 0.08120 -0.1155 0.0029 1.0000 15.500 1.6169 0.09726 0.09210 -0.1186 0.0031 1.0000 16.000 1.6008 0.10915 0.10427 -0.1229 0.0032 1.0000 16.500 1.5831 0.12176 0.11716 -0.1282 0.0033 1.0000 17.000 1.5658 0.13452 0.13016 -0.1343 0.0034 1.0000 17.500 1.5501 0.14697 0.14280 -0.1408 0.0035 1.0000 18.000 1.5418 0.15774 0.15373 -0.1467 0.0036 1.0000 18.500 1.5429 0.16711 0.16334 -0.1523 0.0038 1.0000 19.000 1.5431 0.17628 0.17274 -0.1578 0.0042 1.0000 19.500 1.5419 0.18553 0.18217 -0.1637 0.0044 1.0000 20.000 1.5488 0.19194 0.18866 -0.1674 0.0048 1.0000 20.500 1.5524 0.20035 0.19727 -0.1732 0.0052 1.0000 21.000 1.5454 0.21176 0.20904 -0.1814 0.0056 1.0000 21.500 1.5336 0.22442 0.22199 -0.1910 0.0057 1.0000 22.000 1.5182 0.23860 0.23646 -0.2019 0.0059 1.0000 22.500 1.4970 0.25570 0.25385 -0.2149 0.0059 1.0000 23.000 1.4612 0.28089 0.27931 -0.2327 0.0056 1.0000 24.500 1.0992 0.41769 0.41657 -0.2318 0.0108 1.0000 25.000 1.1008 0.43391 0.43279 -0.2359 0.0094 1.0000 25.500 1.1053 0.44435 0.44324 -0.2385 0.0087 1.0000 26.000 1.1080 0.45835 0.45725 -0.2417 0.0081 1.0000 26.500 1.1115 0.47074 0.46966 -0.2446 0.0070 1.0000 27.000 1.1152 0.48044 0.47939 -0.2469 0.0066 1.0000 27.500 1.1169 0.49663 0.49558 -0.2502 0.0058 1.0000 28.000 1.1196 0.50863 0.50760 -0.2530 0.0053 1.0000 28.500 1.1220 0.51872 0.51771 -0.2554 0.0050 1.0000 29.000 1.1235 0.53170 0.53070 -0.2580 0.0049 1.0000 29.500 1.1250 0.54700 0.54602 -0.2610 0.0044 1.0000 30.000 1.1263 0.55963 0.55867 -0.2635 0.0040 1.0000 30.500 1.1273 0.57132 0.57038 -0.2660 0.0038 1.0000 31.000 1.1276 0.58135 0.58043 -0.2682 0.0036 1.0000 31.500 1.1277 0.59396 0.59306 -0.2706 0.0035 1.0000 32.000 1.1275 0.60737 0.60649 -0.2732 0.0035 1.0000 32.500 1.1277 0.62232 0.62146 -0.2758 0.0034 1.0000 33.000 1.1270 0.63438 0.63355 -0.2781 0.0033 1.0000 33.500 1.1261 0.64702 0.64621 -0.2804 0.0030 1.0000 34.000 1.1247 0.65883 0.65804 -0.2826 0.0030 1.0000 34.500 1.1230 0.67040 0.66963 -0.2848 0.0030 1.0000 35.000 1.1211 0.68226 0.68152 -0.2871 0.0028 1.0000 35.500 1.1185 0.69326 0.69254 -0.2892 0.0027 1.0000 36.000 1.1159 0.70462 0.70392 -0.2913 0.0027 1.0000 36.500 1.1127 0.71505 0.71437 -0.2933 0.0026 1.0000 37.000 1.1093 0.72584 0.72520 -0.2953 0.0026 1.0000 37.500 1.1056 0.73621 0.73559 -0.2973 0.0026 1.0000 38.000 1.1011 0.74565 0.74505 -0.2992 0.0025 1.0000 38.500 1.0966 0.75538 0.75480 -0.3011 0.0025 1.0000 39.000 1.0917 0.76475 0.76420 -0.3029 0.0025 1.0000 39.500 1.0866 0.77432 0.77379 -0.3046 0.0025 1.0000 41.500 1.0643 0.81276 0.81232 -0.3116 0.0024 1.0000 42.000 1.0591 0.82387 0.82345 -0.3131 0.0024 1.0000 42.500 1.0529 0.83311 0.83271 -0.3146 0.0022 1.0000 43.000 1.0463 0.84160 0.84122 -0.3161 0.0020 1.0000 43.500 1.0393 0.84951 0.84914 -0.3175 0.0019 1.0000 44.000 1.0317 0.85605 0.85570 -0.3189 0.0017 1.0000 45.000 1.0149 0.86703 0.86673 -0.3217 0.0016 1.0000 46.000 0.9999 0.88448 0.88420 -0.3240 0.0015 1.0000 46.500 0.9921 0.89167 0.89140 -0.3251 0.0015 1.0000 47.000 0.9836 0.89724 0.89700 -0.3260 0.0014 1.0000 47.500 0.9750 0.90301 0.90278 -0.3271 0.0012 1.0000 48.000 0.9658 0.90721 0.90700 -0.3281 0.0011 1.0000 48.500 0.9564 0.91093 0.91074 -0.3291 0.0010 1.0000 49.000 0.9463 0.91289 0.91271 -0.3301 0.0009 1.0000 49.500 0.9358 0.91453 0.91438 -0.3311 0.0009 1.0000 51.000 0.9055 0.92340 0.92328 -0.3333 0.0009 1.0000 51.500 0.8958 0.92666 0.92655 -0.3339 0.0008 1.0000 52.000 0.8855 0.92808 0.92799 -0.3344 0.0008 1.0000 52.500 0.8752 0.92957 0.92949 -0.3348 0.0008 1.0000 53.000 0.8647 0.93058 0.93052 -0.3353 0.0008 1.0000 53.500 0.8535 0.92945 0.92940 -0.3358 0.0007 1.0000 54.000 0.8422 0.92814 0.92811 -0.3362 0.0006 1.0000 54.500 0.8307 0.92599 0.92597 -0.3366 0.0006 1.0000 55.000 0.8191 0.92379 0.92378 -0.3369 0.0005 1.0000 55.500 0.8072 0.92024 0.92024 -0.3372 0.0005 1.0000 56.000 0.7953 0.91664 0.91666 -0.3375 0.0004 1.0000 56.500 0.7831 0.91224 0.91228 -0.3378 0.0004 1.0000 57.000 0.7707 0.90683 0.90687 -0.3380 0.0004 1.0000 57.500 0.7577 0.90099 0.90105 -0.3383 0.0004 1.0000 59.500 0.7096 0.88123 0.88133 -0.3378 0.0003 1.0000 60.000 0.6971 0.87401 0.87411 -0.3377 0.0003 1.0000