EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 50,000 Max Cl/Cd: 27.02 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e668-il-50000-n5.txt Download as CSV file: xf-e668-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 668 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3757 0.11258 0.10613 -0.0580 0.9803 0.0438
-9.500 -0.3727 0.10939 0.10295 -0.0587 0.9775 0.0434
-9.250 -0.3738 0.10524 0.09884 -0.0607 0.9745 0.0432
-9.000 -0.3740 0.10087 0.09451 -0.0632 0.9717 0.0429
-8.750 -0.3800 0.09672 0.09039 -0.0649 0.9681 0.0426
-8.500 -0.3895 0.09228 0.08600 -0.0667 0.9642 0.0422
-8.250 -0.3989 0.08744 0.08118 -0.0698 0.9604 0.0415
-8.000 -0.4161 0.08306 0.07680 -0.0717 0.9559 0.0409
-7.750 -0.4347 0.07902 0.07273 -0.0721 0.9508 0.0404
-7.500 -0.4472 0.07408 0.06764 -0.0737 0.9463 0.0401
-7.250 -0.4546 0.06934 0.06267 -0.0749 0.9421 0.0396
-7.000 -0.4629 0.06527 0.05835 -0.0742 0.9375 0.0394
-6.750 -0.4615 0.06089 0.05359 -0.0746 0.9336 0.0393
-6.500 -0.4511 0.05660 0.04882 -0.0756 0.9304 0.0396
-6.250 -0.4380 0.05287 0.04460 -0.0760 0.9275 0.0402
-6.000 -0.4269 0.04991 0.04115 -0.0751 0.9238 0.0415
-5.750 -0.4082 0.04672 0.03719 -0.0750 0.9207 0.0439
-5.500 -0.3860 0.04501 0.03538 -0.0754 0.9178 0.0470
-5.250 -0.3590 0.04288 0.03278 -0.0759 0.9154 0.0498
-5.000 -0.3300 0.04116 0.03074 -0.0768 0.9133 0.0551
-4.750 -0.3127 0.03993 0.02927 -0.0752 0.9096 0.0601
-4.500 -0.2910 0.03880 0.02802 -0.0745 0.9061 0.0666
-4.250 -0.2657 0.03775 0.02680 -0.0742 0.9029 0.0762
-4.000 -0.2384 0.03686 0.02583 -0.0743 0.9002 0.0895
-3.750 -0.2085 0.03604 0.02496 -0.0749 0.8977 0.1107
-3.500 -0.1922 0.03531 0.02429 -0.0735 0.8932 0.1350
-3.250 -0.1703 0.03449 0.02369 -0.0732 0.8893 0.1803
-3.000 -0.1439 0.03357 0.02324 -0.0740 0.8859 0.2689
-2.750 -0.1167 0.03263 0.02308 -0.0747 0.8830 0.4230
-2.500 -0.1066 0.03230 0.02353 -0.0707 0.8787 0.5727
-2.250 -0.1024 0.03258 0.02417 -0.0644 0.8731 0.6872
-2.000 -0.0866 0.03310 0.02457 -0.0609 0.8686 0.7736
-1.750 -0.0720 0.03352 0.02479 -0.0574 0.8643 0.8283
-1.500 -0.0656 0.03368 0.02483 -0.0527 0.8579 0.8689
-1.250 -0.0429 0.03385 0.02483 -0.0508 0.8535 0.9115
-1.000 0.0123 0.03426 0.02493 -0.0555 0.8510 0.9541
-0.750 0.0835 0.03482 0.02512 -0.0646 0.8479 0.9866
-0.500 0.1074 0.03502 0.02513 -0.0653 0.8413 1.0000
-0.250 0.1288 0.03517 0.02507 -0.0650 0.8361 1.0000
0.000 0.1356 0.03531 0.02507 -0.0625 0.8283 1.0000
0.250 0.1580 0.03556 0.02515 -0.0624 0.8224 1.0000
0.500 0.1823 0.03588 0.02529 -0.0626 0.8169 1.0000
0.750 0.1987 0.03620 0.02548 -0.0616 0.8090 1.0000
1.000 0.2317 0.03657 0.02569 -0.0631 0.8045 1.0000
1.250 0.2458 0.03698 0.02601 -0.0619 0.7957 1.0000
1.500 0.2766 0.03736 0.02626 -0.0631 0.7902 1.0000
1.750 0.2968 0.03781 0.02662 -0.0627 0.7824 1.0000
2.000 0.3244 0.03821 0.02694 -0.0634 0.7758 1.0000
2.250 0.3502 0.03864 0.02729 -0.0637 0.7689 1.0000
2.500 0.3741 0.03906 0.02766 -0.0639 0.7610 1.0000
2.750 0.4011 0.03947 0.02802 -0.0643 0.7541 1.0000
3.000 0.4251 0.03988 0.02841 -0.0644 0.7458 1.0000
3.250 0.4482 0.04032 0.02882 -0.0644 0.7375 1.0000
3.500 0.4775 0.04061 0.02910 -0.0651 0.7303 1.0000
3.750 0.4970 0.04111 0.02961 -0.0646 0.7205 1.0000
4.000 0.5310 0.04124 0.02976 -0.0657 0.7147 1.0000
4.250 0.5481 0.04180 0.03034 -0.0649 0.7036 1.0000
4.500 0.5751 0.04207 0.03064 -0.0652 0.6956 1.0000
4.750 0.6014 0.04232 0.03093 -0.0653 0.6867 1.0000
5.000 0.6208 0.04282 0.03151 -0.0647 0.6758 1.0000
5.250 0.6567 0.04264 0.03140 -0.0657 0.6699 1.0000
5.500 0.6737 0.04322 0.03204 -0.0648 0.6576 1.0000
5.750 0.6947 0.04363 0.03256 -0.0643 0.6464 1.0000
6.000 0.7303 0.04325 0.03228 -0.0650 0.6398 1.0000
6.250 0.7481 0.04377 0.03290 -0.0641 0.6270 1.0000
6.500 0.7691 0.04412 0.03336 -0.0635 0.6151 1.0000
6.750 0.8071 0.04331 0.03271 -0.0640 0.6089 1.0000
7.000 0.8261 0.04368 0.03321 -0.0631 0.5956 1.0000
7.250 0.8471 0.04389 0.03355 -0.0623 0.5828 1.0000
7.500 0.8722 0.04376 0.03359 -0.0616 0.5711 1.0000
7.750 0.9096 0.04258 0.03258 -0.0616 0.5630 1.0000
8.000 0.9319 0.04260 0.03278 -0.0607 0.5488 1.0000
8.250 0.9560 0.04246 0.03279 -0.0598 0.5345 1.0000
8.500 0.9819 0.04215 0.03264 -0.0590 0.5197 1.0000
8.750 1.0094 0.04169 0.03236 -0.0582 0.5039 1.0000
9.000 1.0382 0.04114 0.03194 -0.0575 0.4867 1.0000
9.250 1.0671 0.04059 0.03150 -0.0567 0.4675 1.0000
9.500 1.0835 0.04113 0.03216 -0.0553 0.4453 1.0000
9.750 1.1079 0.04101 0.03208 -0.0542 0.4225 1.0000
10.000 1.1218 0.04181 0.03294 -0.0527 0.3982 1.0000
10.250 1.1395 0.04230 0.03339 -0.0513 0.3739 1.0000
10.500 1.1482 0.04360 0.03477 -0.0496 0.3494 1.0000
10.750 1.1587 0.04475 0.03588 -0.0480 0.3255 1.0000
11.000 1.1652 0.04634 0.03750 -0.0464 0.3021 1.0000
11.250 1.1720 0.04790 0.03900 -0.0448 0.2800 1.0000
11.500 1.1759 0.04985 0.04100 -0.0434 0.2583 1.0000
11.750 1.1798 0.05183 0.04296 -0.0420 0.2382 1.0000
12.000 1.1831 0.05394 0.04504 -0.0407 0.2196 1.0000
12.250 1.1855 0.05628 0.04744 -0.0395 0.2017 1.0000
12.500 1.1874 0.05875 0.04994 -0.0385 0.1851 1.0000
12.750 1.1892 0.06132 0.05254 -0.0377 0.1699 1.0000
13.000 1.1907 0.06401 0.05526 -0.0369 0.1561 1.0000
13.250 1.1922 0.06678 0.05806 -0.0363 0.1437 1.0000
13.500 1.1936 0.06960 0.06087 -0.0358 0.1326 1.0000
13.750 1.1948 0.07267 0.06412 -0.0355 0.1219 1.0000
14.000 1.1964 0.07578 0.06735 -0.0353 0.1126 1.0000
14.250 1.1983 0.07877 0.07033 -0.0351 0.1046 1.0000
14.500 1.1988 0.08220 0.07399 -0.0352 0.0969 1.0000
14.750 1.2007 0.08545 0.07732 -0.0353 0.0904 1.0000
15.000 1.2000 0.08913 0.08120 -0.0357 0.0844 1.0000
15.250 1.2025 0.09238 0.08450 -0.0360 0.0794 1.0000
15.500 1.1983 0.09688 0.08932 -0.0369 0.0749 1.0000
15.750 1.2001 0.10019 0.09268 -0.0375 0.0707 1.0000
16.000 1.1959 0.10488 0.09761 -0.0388 0.0675 1.0000
16.250 1.1859 0.11068 0.10373 -0.0409 0.0650 1.0000
16.500 1.1780 0.11611 0.10937 -0.0431 0.0625 1.0000
16.750 1.1873 0.11813 0.11128 -0.0434 0.0591 1.0000
17.000 1.1688 0.12600 0.11949 -0.0474 0.0583 1.0000
17.250 1.1479 0.13483 0.12861 -0.0524 0.0578 1.0000
17.500 1.1231 0.14519 0.13920 -0.0587 0.0578 1.0000
17.750 1.0943 0.15763 0.15179 -0.0665 0.0581 1.0000
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