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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.0720 0.08334 0.08092 -0.1133 0.8292 0.0104 -11.250 -0.0746 0.07865 0.07624 -0.1148 0.8275 0.0105 -11.000 -0.2292 0.07143 0.06902 -0.1187 0.8358 0.0061 -10.750 -0.4698 0.02429 0.02015 -0.1428 0.8261 0.0046 -10.500 -0.4570 0.02186 0.01744 -0.1439 0.8235 0.0046 -10.250 -0.4384 0.02020 0.01555 -0.1448 0.8211 0.0046 -10.000 -0.4174 0.01891 0.01407 -0.1454 0.8188 0.0047 -9.750 -0.3946 0.01787 0.01287 -0.1459 0.8163 0.0048 -9.500 -0.3714 0.01692 0.01181 -0.1464 0.8146 0.0049 -9.250 -0.3471 0.01611 0.01089 -0.1468 0.8127 0.0050 -9.000 -0.3221 0.01536 0.01004 -0.1473 0.8109 0.0052 -8.750 -0.2965 0.01467 0.00926 -0.1478 0.8090 0.0055 -8.500 -0.2703 0.01407 0.00857 -0.1483 0.8071 0.0058 -8.250 -0.2431 0.01362 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0.00220 -0.1731 0.7736 0.5093 -3.250 0.3745 0.00649 0.00222 -0.1747 0.7717 0.5716 -3.000 0.4051 0.00646 0.00225 -0.1754 0.7702 0.6021 -2.750 0.4351 0.00648 0.00227 -0.1760 0.7684 0.6172 -2.500 0.4651 0.00651 0.00228 -0.1766 0.7665 0.6277 -2.250 0.4947 0.00657 0.00234 -0.1771 0.7645 0.6394 -2.000 0.5238 0.00669 0.00247 -0.1773 0.7624 0.6535 -1.750 0.5539 0.00677 0.00248 -0.1779 0.7602 0.6592 -1.500 0.5836 0.00682 0.00251 -0.1785 0.7575 0.6622 -1.250 0.6123 0.00682 0.00253 -0.1788 0.7553 0.6649 -1.000 0.6413 0.00683 0.00254 -0.1792 0.7526 0.6679 -0.750 0.6707 0.00685 0.00253 -0.1797 0.7498 0.6709 -0.500 0.7005 0.00686 0.00252 -0.1803 0.7472 0.6735 -0.250 0.7300 0.00687 0.00251 -0.1808 0.7448 0.6759 0.000 0.7595 0.00693 0.00256 -0.1813 0.7424 0.6779 0.250 0.7881 0.00694 0.00260 -0.1817 0.7400 0.6801 0.500 0.8171 0.00696 0.00264 -0.1821 0.7375 0.6824 0.750 0.8462 0.00698 0.00267 -0.1825 0.7348 0.6848 1.000 0.8755 0.00700 0.00268 -0.1830 0.7320 0.6871 1.250 0.9051 0.00706 0.00270 -0.1836 0.7288 0.6891 1.500 0.9334 0.00703 0.00273 -0.1839 0.7251 0.6911 1.750 0.9615 0.00701 0.00274 -0.1841 0.7203 0.6929 2.000 0.9896 0.00703 0.00275 -0.1843 0.7152 0.6947 2.250 1.0176 0.00705 0.00281 -0.1845 0.7101 0.6967 2.500 1.0456 0.00706 0.00284 -0.1847 0.7045 0.6986 2.750 1.0736 0.00712 0.00288 -0.1849 0.6989 0.7006 3.000 1.1017 0.00714 0.00295 -0.1852 0.6926 0.7025 3.250 1.1289 0.00720 0.00298 -0.1852 0.6842 0.7042 3.500 1.1560 0.00723 0.00303 -0.1853 0.6740 0.7061 3.750 1.1822 0.00730 0.00311 -0.1851 0.6614 0.7078 4.000 1.2061 0.00746 0.00321 -0.1845 0.6417 0.7094 4.250 1.2304 0.00764 0.00336 -0.1839 0.6225 0.7113 4.500 1.2544 0.00785 0.00353 -0.1833 0.6045 0.7132 5.000 1.2991 0.00842 0.00397 -0.1816 0.5607 0.7169 5.250 1.3162 0.00894 0.00431 -0.1797 0.5249 0.7187 5.500 1.3298 0.00959 0.00474 -0.1772 0.4784 0.7204 5.750 1.3406 0.01033 0.00525 -0.1741 0.4283 0.7222 6.000 1.3482 0.01113 0.00582 -0.1705 0.3808 0.7239 6.250 1.3504 0.01204 0.00647 -0.1659 0.3267 0.7256 6.500 1.3548 0.01304 0.00722 -0.1619 0.2797 0.7275 6.750 1.3621 0.01395 0.00795 -0.1586 0.2435 0.7295 7.000 1.3697 0.01489 0.00872 -0.1554 0.2092 0.7314 7.250 1.3752 0.01598 0.00961 -0.1521 0.1714 0.7331 7.500 1.3813 0.01711 0.01058 -0.1490 0.1394 0.7346 7.750 1.3899 0.01816 0.01151 -0.1464 0.1152 0.7364 8.000 1.4004 0.01914 0.01242 -0.1442 0.0966 0.7380 8.250 1.4107 0.02016 0.01337 -0.1421 0.0806 0.7398 8.500 1.4228 0.02111 0.01428 -0.1402 0.0688 0.7417 8.750 1.4353 0.02205 0.01520 -0.1385 0.0592 0.7435 9.000 1.4477 0.02303 0.01615 -0.1368 0.0506 0.7453 9.250 1.4591 0.02409 0.01719 -0.1351 0.0420 0.7469 9.500 1.4701 0.02519 0.01826 -0.1333 0.0343 0.7484 9.750 1.4813 0.02629 0.01934 -0.1316 0.0278 0.7501 10.000 1.4915 0.02746 0.02051 -0.1299 0.0221 0.7520 10.250 1.5020 0.02863 0.02168 -0.1282 0.0178 0.7538 10.500 1.5109 0.02994 0.02299 -0.1263 0.0133 0.7555 10.750 1.5185 0.03134 0.02439 -0.1244 0.0080 0.7572 11.000 1.5237 0.03297 0.02601 -0.1222 0.0044 0.7589 11.250 1.5322 0.03438 0.02748 -0.1205 0.0037 0.7606 11.500 1.5409 0.03579 0.02895 -0.1188 0.0033 0.7623 11.750 1.5499 0.03720 0.03042 -0.1173 0.0031 0.7639 12.000 1.5586 0.03865 0.03197 -0.1157 0.0030 0.7660 12.250 1.5669 0.04017 0.03357 -0.1142 0.0029 0.7678 12.500 1.5739 0.04182 0.03531 -0.1127 0.0027 0.7695 12.750 1.5795 0.04364 0.03721 -0.1111 0.0026 0.7713 13.000 1.5856 0.04542 0.03907 -0.1096 0.0025 0.7731 13.250 1.5877 0.04763 0.04138 -0.1078 0.0023 0.7749 13.500 1.5891 0.04997 0.04383 -0.1061 0.0022 0.7765 13.750 1.5875 0.05267 0.04665 -0.1043 0.0022 0.7781 14.000 1.5919 0.05482 0.04890 -0.1031 0.0021 0.7802 14.250 1.5949 0.05714 0.05132 -0.1019 0.0021 0.7823 14.500 1.5962 0.05971 0.05400 -0.1007 0.0021 0.7843 14.750 1.5967 0.06243 0.05683 -0.0996 0.0020 0.7863 15.000 1.5960 0.06535 0.05985 -0.0986 0.0019 0.7882 15.250 1.5951 0.06834 0.06296 -0.0977 0.0019 0.7902 15.500 1.5925 0.07159 0.06631 -0.0969 0.0019 0.7920 15.750 1.5894 0.07499 0.06983 -0.0963 0.0019 0.7939 16.000 1.5846 0.07872 0.07368 -0.0958 0.0018 0.7960 16.250 1.5798 0.08250 0.07759 -0.0955 0.0018 0.7981 16.500 1.5732 0.08662 0.08184 -0.0954 0.0018 0.8002 16.750 1.5674 0.09067 0.08602 -0.0955 0.0018 0.8026 17.000 1.5600 0.09506 0.09054 -0.0957 0.0018 0.8050 17.250 1.5512 0.09973 0.09533 -0.0962 0.0018 0.8071 17.500 1.5433 0.10440 0.10014 -0.0970 0.0018 0.8097 17.750 1.5344 0.10931 0.10519 -0.0980 0.0018 0.8122 18.000 1.5242 0.11448 0.11050 -0.0993 0.0018 0.8149 18.250 1.5146 0.11965 0.11579 -0.1008 0.0017 0.8177