XFOIL Version 6.94 Calculated polar for: NASA/LANGLEY NLF 0414F 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 0.2594 0.02057 0.01641 -0.0659 0.7923 0.8142 0.500 0.3184 0.02071 0.01648 -0.0664 0.7908 0.8200 1.500 0.4215 0.02057 0.01637 -0.0669 0.7744 0.8282 2.000 0.4830 0.02008 0.01590 -0.0674 0.7727 0.8305 2.500 0.5482 0.01898 0.01479 -0.0676 0.7707 0.8324 3.000 0.6069 0.01783 0.01371 -0.0682 0.7565 0.8350 3.500 0.6799 0.01528 0.01114 -0.0688 0.7531 0.8361 4.500 0.8035 0.01289 0.00897 -0.0706 0.7180 0.8391 5.000 0.8682 0.01071 0.00643 -0.0703 0.6287 0.8397 5.500 0.8736 0.01375 0.00815 -0.0644 0.3934 0.8407 6.000 0.8774 0.01690 0.01032 -0.0591 0.2167 0.8415 6.500 0.9049 0.01880 0.01172 -0.0565 0.1275 0.8424 7.500 0.9725 0.02181 0.01428 -0.0525 0.0580 0.8427 8.000 1.0075 0.02326 0.01568 -0.0507 0.0497 0.8430 8.500 1.0419 0.02474 0.01719 -0.0488 0.0445 0.8433 9.500 1.1038 0.02829 0.02078 -0.0443 0.0380 0.8434 10.000 1.1383 0.02986 0.02249 -0.0425 0.0359 0.8434 10.500 1.1694 0.03172 0.02436 -0.0404 0.0338 0.8435 12.500 1.3016 0.04002 0.03317 -0.0328 0.0284 0.8444 13.000 1.3285 0.04264 0.03606 -0.0306 0.0272 0.8445 13.500 1.3522 0.04539 0.03901 -0.0286 0.0262 0.8446 14.000 1.3750 0.04851 0.04227 -0.0266 0.0255 0.8447 14.500 1.3893 0.05311 0.04719 -0.0240 0.0248 0.8449 15.000 1.3817 0.05856 0.05312 -0.0207 0.0245 0.8449 15.500 1.3651 0.06533 0.06037 -0.0179 0.0241 0.8449 16.000 1.3379 0.07390 0.06943 -0.0164 0.0239 0.8449 16.500 1.2992 0.08496 0.08097 -0.0172 0.0238 0.8449 17.000 1.2489 0.09947 0.09596 -0.0218 0.0238 0.8448 17.500 1.1866 0.11900 0.11596 -0.0321 0.0240 0.8445 18.000 1.1023 0.14870 0.14609 -0.0521 0.0246 0.8441 20.000 0.6697 0.20916 0.20688 -0.0613 0.0295 0.8452 21.000 0.6721 0.22311 0.22088 -0.0680 0.0268 0.8457 21.500 0.6803 0.22793 0.22573 -0.0702 0.0256 0.8460 22.000 0.6952 0.23200 0.22984 -0.0710 0.0251 0.8464 22.500 0.6864 0.24140 0.23925 -0.0763 0.0234 0.8468 23.000 0.6927 0.24686 0.24476 -0.0788 0.0221 0.8472 24.000 0.7014 0.25995 0.25790 -0.0845 0.0200 0.8483 24.500 0.7073 0.26558 0.26357 -0.0870 0.0186 0.8490 25.500 0.7160 0.27904 0.27709 -0.0926 0.0159 0.8504 26.500 0.7248 0.29251 0.29063 -0.0979 0.0134 0.8523 27.000 0.7303 0.29820 0.29635 -0.1005 0.0123 0.8534 27.500 0.7375 0.30330 0.30149 -0.1023 0.0119 0.8547 28.000 0.7378 0.31276 0.31096 -0.1059 0.0105 0.8559 28.500 0.7428 0.31833 0.31657 -0.1085 0.0096 0.8574 29.000 0.7478 0.32408 0.32236 -0.1107 0.0093 0.8592 29.500 0.7498 0.33333 0.33162 -0.1138 0.0083 0.8609 30.000 0.7536 0.33960 0.33792 -0.1164 0.0075 0.8633 30.500 0.7576 0.34504 0.34341 -0.1189 0.0071 0.8677 31.000 0.7601 0.35219 0.35060 -0.1213 0.0070 0.8734 31.500 0.7627 0.36028 0.35874 -0.1240 0.0060 0.8808 32.000 0.7642 0.36551 0.36411 -0.1258 0.0054 0.9573 32.500 0.7673 0.37079 0.36940 -0.1284 0.0051 1.0000 33.000 0.7693 0.37913 0.37775 -0.1311 0.0049 1.0000 33.500 0.7719 0.38685 0.38548 -0.1336 0.0043 1.0000 34.000 0.7740 0.39324 0.39189 -0.1362 0.0038 1.0000 34.500 0.7759 0.39912 0.39779 -0.1388 0.0036 1.0000 35.000 0.7774 0.40444 0.40313 -0.1413 0.0034 1.0000 35.500 0.7785 0.41221 0.41091 -0.1439 0.0033 1.0000 36.000 0.7800 0.41981 0.41851 -0.1463 0.0029 1.0000 36.500 0.7812 0.42613 0.42485 -0.1489 0.0025 1.0000 37.000 0.7817 0.43161 0.43035 -0.1515 0.0022 1.0000 38.000 0.7820 0.44465 0.44342 -0.1563 0.0020 1.0000 38.500 0.7824 0.45162 0.45040 -0.1587 0.0017 1.0000 39.000 0.7821 0.45749 0.45629 -0.1611 0.0015 1.0000 39.500 0.7815 0.46302 0.46184 -0.1636 0.0013 1.0000 40.000 0.7804 0.46795 0.46679 -0.1661 0.0012 1.0000 40.500 0.7787 0.47243 0.47129 -0.1685 0.0011 1.0000 41.500 0.7760 0.48448 0.48337 -0.1732 0.0011 1.0000 42.000 0.7744 0.49009 0.48899 -0.1754 0.0011 1.0000 42.500 0.7726 0.49539 0.49432 -0.1777 0.0010 1.0000 43.000 0.7704 0.50031 0.49926 -0.1799 0.0009 1.0000 43.500 0.7679 0.50503 0.50399 -0.1822 0.0008 1.0000 44.000 0.7652 0.50941 0.50839 -0.1845 0.0008 1.0000 44.500 0.7621 0.51357 0.51258 -0.1867 0.0007 1.0000 45.000 0.7587 0.51733 0.51636 -0.1890 0.0006 1.0000 45.500 0.7552 0.52086 0.51992 -0.1913 0.0006 1.0000 46.000 0.7511 0.52393 0.52301 -0.1936 0.0005 1.0000 46.500 0.7466 0.52666 0.52575 -0.1959 0.0005 1.0000 48.000 0.7342 0.53804 0.53718 -0.2021 0.0005 1.0000 48.500 0.7297 0.54118 0.54035 -0.2040 0.0004 1.0000 49.000 0.7249 0.54404 0.54323 -0.2060 0.0004 1.0000 49.500 0.7198 0.54659 0.54579 -0.2081 0.0003 1.0000 50.000 0.7144 0.54871 0.54794 -0.2101 0.0003 1.0000 50.500 0.7088 0.55057 0.54981 -0.2121 0.0003 1.0000 51.000 0.7031 0.55217 0.55144 -0.2141 0.0002 1.0000 51.500 0.6970 0.55342 0.55270 -0.2160 0.0002 1.0000 52.000 0.6908 0.55445 0.55376 -0.2180 0.0002 1.0000 52.500 0.6844 0.55522 0.55454 -0.2199 0.0002 1.0000 53.000 0.6778 0.55567 0.55502 -0.2218 0.0002 1.0000 53.500 0.6709 0.55584 0.55521 -0.2237 0.0001 1.0000 54.000 0.6639 0.55575 0.55514 -0.2257 0.0001 1.0000 54.500 0.6562 0.55507 0.55447 -0.2276 0.0001 1.0000 56.000 0.6351 0.55537 0.55482 -0.2325 0.0001 1.0000 56.500 0.6278 0.55504 0.55452 -0.2341 0.0001 1.0000 57.000 0.6202 0.55419 0.55368 -0.2357 0.0001 1.0000 57.500 0.6123 0.55291 0.55242 -0.2373 0.0001 1.0000 58.000 0.6044 0.55148 0.55100 -0.2389 0.0000 1.0000 58.500 0.5961 0.54948 0.54902 -0.2405 0.0000 1.0000 60.000 0.5713 0.54384 0.54342 -0.2449 0.0000 1.0000