EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 100,000 Max Cl/Cd: 32.77 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e639-il-100000.txt Download as CSV file: xf-e639-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 639 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2563 0.09603 0.09183 -0.0314 1.0000 0.0723
-8.250 -0.2565 0.09339 0.08929 -0.0320 1.0000 0.0742
-8.000 -0.2615 0.09103 0.08707 -0.0330 1.0000 0.0763
-7.750 -0.2747 0.08924 0.08547 -0.0338 1.0000 0.0776
-7.500 -0.2904 0.08774 0.08417 -0.0385 0.9873 0.0786
-7.250 -0.2669 0.08147 0.07774 -0.0532 0.9530 0.0804
-7.000 -0.2269 0.07607 0.07247 -0.0506 0.9402 0.0861
-6.750 -0.2020 0.07228 0.06820 -0.0668 0.9077 0.0945
-6.500 -0.1718 0.06552 0.06152 -0.0683 0.8869 0.0979
-6.250 -0.1500 0.06223 0.05809 -0.0697 0.8596 0.1032
-6.000 -0.1462 0.06051 0.05580 -0.0734 0.8349 0.1111
-5.750 -0.1279 0.05629 0.05169 -0.0720 0.8139 0.1144
-5.500 -0.1142 0.05419 0.04938 -0.0718 0.7950 0.1229
-5.250 -0.1035 0.05128 0.04627 -0.0715 0.7786 0.1299
-5.000 -0.0919 0.04981 0.04441 -0.0711 0.7631 0.1430
-4.750 -0.0755 0.04681 0.04147 -0.0697 0.7483 0.1494
-4.500 -0.0616 0.04467 0.03916 -0.0688 0.7347 0.1639
-4.250 -0.0469 0.04287 0.03720 -0.0676 0.7221 0.1840
-4.000 -0.0335 0.04089 0.03511 -0.0661 0.7109 0.2106
-3.750 -0.0197 0.03913 0.03331 -0.0642 0.6997 0.2436
-3.000 0.0207 0.03404 0.02817 -0.0570 0.6693 0.3655
-2.750 0.0952 0.03138 0.02304 -0.0615 0.6610 0.1254
-2.500 0.1259 0.02864 0.01974 -0.0600 0.6532 0.0926
-2.250 0.1512 0.02696 0.01785 -0.0591 0.6439 0.0873
-2.000 0.1788 0.02576 0.01626 -0.0582 0.6366 0.0856
-1.750 0.2058 0.02484 0.01502 -0.0572 0.6274 0.0824
-1.500 0.2348 0.02403 0.01392 -0.0565 0.6209 0.0810
-1.250 0.2610 0.02326 0.01312 -0.0558 0.6123 0.0813
-1.000 0.2885 0.02241 0.01221 -0.0553 0.6060 0.0833
-0.750 0.3124 0.02199 0.01187 -0.0544 0.5981 0.0891
-0.500 0.4640 0.01782 0.01017 -0.0760 0.5873 1.0000
-0.250 0.4855 0.01810 0.01017 -0.0749 0.5802 1.0000
0.000 0.5086 0.01831 0.01007 -0.0739 0.5749 1.0000
0.250 0.5289 0.01869 0.01036 -0.0728 0.5680 1.0000
0.500 0.5510 0.01897 0.01046 -0.0718 0.5623 1.0000
0.750 0.5737 0.01930 0.01060 -0.0709 0.5578 1.0000
1.000 0.5933 0.01977 0.01105 -0.0697 0.5513 1.0000
1.250 0.6157 0.02007 0.01121 -0.0687 0.5462 1.0000
1.500 0.6375 0.02048 0.01150 -0.0677 0.5415 1.0000
1.750 0.6566 0.02102 0.01205 -0.0665 0.5357 1.0000
2.000 0.6788 0.02140 0.01233 -0.0656 0.5312 1.0000
2.250 0.7018 0.02181 0.01261 -0.0647 0.5273 1.0000
2.500 0.7184 0.02253 0.01342 -0.0633 0.5212 1.0000
2.750 0.7402 0.02295 0.01377 -0.0623 0.5167 1.0000
3.000 0.7642 0.02332 0.01402 -0.0615 0.5133 1.0000
3.250 0.7788 0.02428 0.01510 -0.0599 0.5079 1.0000
3.500 0.7982 0.02490 0.01573 -0.0587 0.5031 1.0000
3.750 0.8221 0.02524 0.01598 -0.0580 0.4994 1.0000
4.000 0.8398 0.02607 0.01684 -0.0566 0.4951 1.0000
4.250 0.8531 0.02717 0.01808 -0.0549 0.4899 1.0000
4.500 0.8747 0.02770 0.01858 -0.0540 0.4860 1.0000
4.750 0.9009 0.02800 0.01878 -0.0536 0.4829 1.0000
5.000 0.9063 0.02966 0.02065 -0.0511 0.4771 1.0000
5.250 0.9215 0.03068 0.02175 -0.0496 0.4726 1.0000
5.500 0.9463 0.03105 0.02208 -0.0491 0.4694 1.0000
5.750 0.9656 0.03187 0.02292 -0.0480 0.4656 1.0000
6.000 0.9610 0.03429 0.02557 -0.0449 0.4590 1.0000
6.250 0.9815 0.03498 0.02628 -0.0439 0.4554 1.0000
6.500 1.0138 0.03490 0.02616 -0.0441 0.4528 1.0000
6.750 0.9832 0.03939 0.03095 -0.0393 0.4449 1.0000
7.000 0.9989 0.04040 0.03201 -0.0380 0.4406 1.0000
7.250 1.0357 0.03992 0.03151 -0.0383 0.4382 1.0000
7.500 0.9020 0.05279 0.04462 -0.0294 0.4246 1.0000
7.750 0.9739 0.04930 0.04116 -0.0307 0.4237 1.0000
8.000 1.0381 0.04651 0.03839 -0.0320 0.4226 1.0000
8.250 0.7648 0.07610 0.06794 -0.0298 0.4019 1.0000
8.500 0.7618 0.07945 0.07132 -0.0299 0.3966 1.0000
8.750 0.8188 0.07650 0.06843 -0.0281 0.3927 1.0000
9.000 0.7634 0.08567 0.07760 -0.0299 0.3866 1.0000
9.250 0.7720 0.08781 0.07980 -0.0296 0.3808 1.0000
9.500 0.8485 0.08264 0.07469 -0.0269 0.3769 1.0000
9.750 0.7688 0.09460 0.08666 -0.0301 0.3697 1.0000
10.000 0.8189 0.09214 0.08426 -0.0281 0.3633 1.0000
10.250 0.7849 0.09908 0.09123 -0.0298 0.3562 1.0000
10.500 0.8060 0.09994 0.09214 -0.0292 0.3501 1.0000
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Polar data table (+)
Polar graphs
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