XFOIL Version 6.96 Calculated polar for: FX 62-K-153/20 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 ------ -------- --------- --------- -------- -------- -------- -14.250 -0.5727 0.05632 0.05344 -0.1214 0.8353 0.0024 -14.000 -0.6045 0.04702 0.04388 -0.1286 0.8305 0.0024 -13.750 -0.6223 0.04135 0.03801 -0.1323 0.8263 0.0024 -13.500 -0.6317 0.03728 0.03374 -0.1344 0.8220 0.0024 -13.250 -0.6363 0.03401 0.03027 -0.1358 0.8179 0.0024 -13.000 -0.6364 0.03131 0.02738 -0.1367 0.8144 0.0024 -12.750 -0.6329 0.02899 0.02489 -0.1373 0.8112 0.0024 -12.500 -0.6258 0.02704 0.02278 -0.1377 0.8082 0.0024 -12.250 -0.6162 0.02532 0.02090 -0.1380 0.8054 0.0024 -12.000 -0.6042 0.02381 0.01923 -0.1383 0.8029 0.0024 -11.750 -0.5914 0.02248 0.01777 -0.1383 0.8007 0.0024 -11.500 -0.5749 0.02129 0.01646 -0.1387 0.7986 0.0024 -11.250 -0.5552 0.02018 0.01522 -0.1395 0.7964 0.0025 -11.000 -0.5337 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-0.1812 0.5690 0.6777 3.750 1.1575 0.00810 0.00312 -0.1803 0.5417 0.6795 4.000 1.1745 0.00869 0.00349 -0.1784 0.4960 0.6814 4.250 1.1903 0.00933 0.00390 -0.1763 0.4489 0.6833 4.500 1.2090 0.00982 0.00424 -0.1748 0.4164 0.6852 4.750 1.2282 0.01026 0.00457 -0.1734 0.3908 0.6870 5.000 1.2472 0.01070 0.00492 -0.1720 0.3654 0.6887 5.250 1.2610 0.01132 0.00536 -0.1696 0.3263 0.6903 5.500 1.2681 0.01206 0.00591 -0.1659 0.2859 0.6919 5.750 1.2763 0.01291 0.00655 -0.1626 0.2440 0.6935 6.000 1.2844 0.01379 0.00724 -0.1594 0.2045 0.6953 6.250 1.2918 0.01474 0.00799 -0.1561 0.1640 0.6971 6.500 1.2991 0.01574 0.00881 -0.1530 0.1305 0.6990 6.750 1.3094 0.01664 0.00958 -0.1505 0.1057 0.7007 7.000 1.3231 0.01738 0.01027 -0.1485 0.0911 0.7023 7.250 1.3366 0.01816 0.01099 -0.1467 0.0770 0.7037 7.500 1.3499 0.01899 0.01177 -0.1449 0.0641 0.7051 7.750 1.3633 0.01983 0.01258 -0.1431 0.0535 0.7068 8.000 1.3779 0.02061 0.01336 -0.1416 0.0463 0.7084 8.250 1.3917 0.02147 0.01421 -0.1400 0.0383 0.7101 8.500 1.4046 0.02240 0.01512 -0.1383 0.0308 0.7117 8.750 1.4170 0.02338 0.01607 -0.1366 0.0245 0.7132 9.000 1.4301 0.02433 0.01703 -0.1351 0.0205 0.7148 9.250 1.4436 0.02527 0.01798 -0.1336 0.0172 0.7164 9.500 1.4561 0.02627 0.01900 -0.1321 0.0146 0.7181 10.000 1.4787 0.02850 0.02125 -0.1288 0.0075 0.7210 10.250 1.4850 0.03000 0.02275 -0.1266 0.0030 0.7224 10.500 1.4953 0.03121 0.02401 -0.1250 0.0024 0.7239 10.750 1.5062 0.03240 0.02526 -0.1234 0.0021 0.7254 11.000 1.5176 0.03356 0.02648 -0.1220 0.0020 0.7270 11.250 1.5283 0.03480 0.02779 -0.1205 0.0019 0.7288 11.500 1.5387 0.03607 0.02912 -0.1191 0.0018 0.7305 11.750 1.5477 0.03746 0.03058 -0.1175 0.0017 0.7320 12.000 1.5566 0.03889 0.03207 -0.1160 0.0016 0.7334 12.250 1.5653 0.04037 0.03362 -0.1145 0.0015 0.7347 12.500 1.5729 0.04197 0.03531 -0.1130 0.0014 0.7361 12.750 1.5791 0.04373 0.03715 -0.1115 0.0013 0.7375 13.000 1.5860 0.04543 0.03893 -0.1101 0.0013 0.7391 13.250 1.5913 0.04732 0.04091 -0.1086 0.0012 0.7408 13.500 1.5984 0.04909 0.04277 -0.1073 0.0012 0.7425 13.750 1.6046 0.05098 0.04474 -0.1061 0.0012 0.7443 14.000 1.6109 0.05288 0.04672 -0.1049 0.0012 0.7459 14.250 1.6156 0.05496 0.04888 -0.1038 0.0011 0.7474 14.500 1.6197 0.05714 0.05114 -0.1026 0.0011 0.7488 14.750 1.6236 0.05941 0.05351 -0.1016 0.0011 0.7502 15.000 1.6269 0.06177 0.05597 -0.1006 0.0010 0.7518 15.250 1.6291 0.06431 0.05860 -0.0997 0.0010 0.7533 15.500 1.6307 0.06696 0.06135 -0.0988 0.0010 0.7550 15.750 1.6312 0.06978 0.06427 -0.0981 0.0010 0.7567 16.000 1.6307 0.07275 0.06735 -0.0974 0.0009 0.7585 16.250 1.6304 0.07578 0.07048 -0.0968 0.0009 0.7604 16.500 1.6274 0.07920 0.07401 -0.0963 0.0009 0.7620 17.000 1.6226 0.08610 0.08114 -0.0959 0.0009 0.7654 17.250 1.6179 0.08993 0.08509 -0.0959 0.0008 0.7671 17.500 1.6130 0.09385 0.08912 -0.0961 0.0008 0.7688 17.750 1.6072 0.09799 0.09338 -0.0965 0.0008 0.7706 18.000 1.6002 0.10238 0.09789 -0.0971 0.0008 0.7724 18.250 1.5933 0.10684 0.10247 -0.0979 0.0008 0.7742 18.500 1.5844 0.11169 0.10745 -0.0990 0.0008 0.7759 18.750 1.5750 0.11668 0.11255 -0.1003 0.0008 0.7776 19.000 1.5665 0.12162 0.11761 -0.1018 0.0007 0.7793 19.250 1.5560 0.12701 0.12314 -0.1037 0.0007 0.7812