E201 (11.88%) (e201-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.49 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e201-il-1000000-n5.txt Download as CSV file: xf-e201-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E201 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7049 0.05820 0.05618 -0.0605 1.0000 0.0065
-12.250 -0.7406 0.04689 0.04468 -0.0697 1.0000 0.0065
-12.000 -0.7630 0.03973 0.03734 -0.0761 1.0000 0.0064
-11.750 -0.7855 0.03556 0.03302 -0.0779 1.0000 0.0064
-11.500 -0.7963 0.03259 0.02987 -0.0777 0.9972 0.0065
-11.250 -0.7844 0.02964 0.02666 -0.0799 0.9918 0.0066
-11.000 -0.7669 0.02729 0.02409 -0.0816 0.9872 0.0067
-10.500 -0.7253 0.02342 0.01979 -0.0840 0.9775 0.0069
-10.000 -0.6756 0.02090 0.01695 -0.0857 0.9632 0.0071
-9.750 -0.6486 0.01984 0.01574 -0.0866 0.9521 0.0072
-9.500 -0.6220 0.01872 0.01444 -0.0874 0.9334 0.0073
-9.250 -0.5971 0.01796 0.01350 -0.0874 0.9059 0.0073
-9.000 -0.5760 0.01728 0.01260 -0.0865 0.8766 0.0074
-8.750 -0.5562 0.01643 0.01152 -0.0855 0.8517 0.0075
-8.500 -0.5372 0.01536 0.01024 -0.0844 0.8301 0.0076
-8.250 -0.5162 0.01456 0.00926 -0.0836 0.8110 0.0078
-8.000 -0.4936 0.01394 0.00850 -0.0829 0.7941 0.0079
-7.750 -0.4701 0.01343 0.00786 -0.0823 0.7786 0.0080
-7.500 -0.4459 0.01298 0.00729 -0.0819 0.7645 0.0082
-7.250 -0.4212 0.01258 0.00679 -0.0814 0.7513 0.0084
-7.000 -0.3961 0.01219 0.00631 -0.0811 0.7393 0.0086
-6.750 -0.3704 0.01187 0.00591 -0.0808 0.7286 0.0088
-6.500 -0.3448 0.01154 0.00549 -0.0805 0.7184 0.0092
-6.250 -0.3191 0.01120 0.00506 -0.0802 0.7084 0.0094
-6.000 -0.2930 0.01088 0.00466 -0.0800 0.6996 0.0097
-5.750 -0.2668 0.01059 0.00429 -0.0797 0.6913 0.0099
-5.500 -0.2401 0.01034 0.00397 -0.0796 0.6829 0.0102
-5.250 -0.2133 0.01012 0.00367 -0.0794 0.6755 0.0104
-5.000 -0.1863 0.00991 0.00341 -0.0793 0.6683 0.0106
-4.750 -0.1596 0.00965 0.00307 -0.0791 0.6614 0.0109
-4.500 -0.1326 0.00940 0.00277 -0.0790 0.6545 0.0115
-4.000 -0.0780 0.00906 0.00233 -0.0788 0.6423 0.0128
-3.750 -0.0505 0.00893 0.00216 -0.0787 0.6359 0.0137
-3.500 -0.0229 0.00881 0.00200 -0.0787 0.6304 0.0149
-3.250 0.0047 0.00865 0.00184 -0.0786 0.6247 0.0192
-2.750 0.0589 0.00818 0.00154 -0.0785 0.6141 0.0707
-2.500 0.0863 0.00801 0.00143 -0.0785 0.6087 0.0967
-2.250 0.1134 0.00782 0.00134 -0.0785 0.6037 0.1336
-2.000 0.1409 0.00762 0.00125 -0.0785 0.5988 0.1719
-1.750 0.1680 0.00740 0.00118 -0.0785 0.5937 0.2229
-1.500 0.1952 0.00724 0.00112 -0.0785 0.5889 0.2665
-1.250 0.2222 0.00694 0.00108 -0.0785 0.5843 0.3442
-1.000 0.2495 0.00678 0.00106 -0.0785 0.5792 0.4002
-0.500 0.3052 0.00668 0.00105 -0.0785 0.5699 0.4491
-0.250 0.3332 0.00665 0.00105 -0.0785 0.5648 0.4715
0.000 0.3609 0.00664 0.00106 -0.0785 0.5602 0.4909
0.250 0.3890 0.00660 0.00108 -0.0786 0.5557 0.5102
0.500 0.4169 0.00658 0.00109 -0.0786 0.5505 0.5308
0.750 0.4446 0.00657 0.00112 -0.0786 0.5456 0.5530
1.000 0.4725 0.00654 0.00115 -0.0786 0.5411 0.5762
1.250 0.5002 0.00652 0.00119 -0.0786 0.5356 0.5998
1.500 0.5276 0.00652 0.00124 -0.0785 0.5303 0.6261
1.750 0.5552 0.00648 0.00129 -0.0785 0.5238 0.6564
2.250 0.6090 0.00643 0.00142 -0.0781 0.5084 0.7298
2.500 0.6354 0.00641 0.00149 -0.0778 0.5007 0.7678
2.750 0.6617 0.00638 0.00157 -0.0775 0.4921 0.8075
3.000 0.6868 0.00636 0.00166 -0.0769 0.4826 0.8519
3.250 0.7103 0.00635 0.00176 -0.0758 0.4724 0.9027
3.500 0.7390 0.00637 0.00185 -0.0759 0.4621 0.9555
3.750 0.7753 0.00649 0.00195 -0.0778 0.4497 0.9831
4.000 0.8101 0.00664 0.00205 -0.0795 0.4348 0.9997
4.250 0.8354 0.00682 0.00217 -0.0791 0.4183 1.0000
4.500 0.8602 0.00704 0.00231 -0.0786 0.3989 1.0000
4.750 0.8837 0.00736 0.00250 -0.0779 0.3668 1.0000
5.000 0.9041 0.00793 0.00280 -0.0767 0.3112 1.0000
5.250 0.9239 0.00856 0.00316 -0.0755 0.2576 1.0000
5.500 0.9443 0.00914 0.00352 -0.0743 0.2120 1.0000
5.750 0.9636 0.00980 0.00393 -0.0730 0.1635 1.0000
6.000 0.9835 0.01040 0.00433 -0.0718 0.1247 1.0000
6.250 1.0046 0.01090 0.00468 -0.0708 0.0984 1.0000
6.500 1.0259 0.01136 0.00505 -0.0699 0.0780 1.0000
6.750 1.0470 0.01183 0.00542 -0.0689 0.0595 1.0000
7.000 1.0663 0.01240 0.00587 -0.0676 0.0387 1.0000
7.250 1.0864 0.01290 0.00630 -0.0664 0.0260 1.0000
7.500 1.1035 0.01358 0.00687 -0.0648 0.0099 1.0000
7.750 1.1241 0.01400 0.00729 -0.0636 0.0075 1.0000
8.000 1.1446 0.01440 0.00772 -0.0625 0.0067 1.0000
8.250 1.1643 0.01483 0.00817 -0.0613 0.0059 1.0000
8.500 1.1840 0.01523 0.00861 -0.0601 0.0056 1.0000
8.750 1.2026 0.01566 0.00907 -0.0587 0.0054 1.0000
9.000 1.2189 0.01609 0.00954 -0.0568 0.0051 1.0000
9.250 1.2337 0.01656 0.01005 -0.0548 0.0050 1.0000
9.500 1.2476 0.01708 0.01062 -0.0526 0.0047 1.0000
9.750 1.2613 0.01763 0.01121 -0.0505 0.0046 1.0000
10.000 1.2738 0.01826 0.01189 -0.0483 0.0045 1.0000
10.250 1.2860 0.01893 0.01261 -0.0462 0.0043 1.0000
10.500 1.2968 0.01971 0.01344 -0.0441 0.0042 1.0000
10.750 1.3056 0.02063 0.01442 -0.0418 0.0040 1.0000
11.000 1.3100 0.02188 0.01576 -0.0391 0.0038 1.0000
11.250 1.3206 0.02279 0.01674 -0.0374 0.0038 1.0000
11.500 1.3298 0.02385 0.01787 -0.0357 0.0038 1.0000
11.750 1.3388 0.02498 0.01906 -0.0341 0.0037 1.0000
12.000 1.3485 0.02612 0.02026 -0.0327 0.0036 1.0000
12.250 1.3529 0.02772 0.02195 -0.0311 0.0036 1.0000
12.500 1.3635 0.02890 0.02318 -0.0301 0.0034 1.0000
12.750 1.3694 0.03052 0.02488 -0.0289 0.0034 1.0000
13.000 1.3767 0.03208 0.02651 -0.0279 0.0033 1.0000
13.250 1.3812 0.03395 0.02847 -0.0270 0.0033 1.0000
13.500 1.3854 0.03591 0.03052 -0.0261 0.0032 1.0000
13.750 1.3891 0.03799 0.03267 -0.0254 0.0031 1.0000
14.000 1.3910 0.04031 0.03509 -0.0248 0.0031 1.0000
14.250 1.3940 0.04258 0.03744 -0.0244 0.0031 1.0000
14.500 1.3947 0.04517 0.04012 -0.0241 0.0030 1.0000
14.750 1.3962 0.04775 0.04279 -0.0239 0.0030 1.0000
15.000 1.3955 0.05066 0.04579 -0.0238 0.0030 1.0000
15.250 1.3952 0.05362 0.04885 -0.0240 0.0029 1.0000
15.500 1.3923 0.05703 0.05236 -0.0243 0.0029 1.0000
15.750 1.3913 0.06029 0.05572 -0.0248 0.0028 1.0000
16.000 1.3900 0.06368 0.05920 -0.0254 0.0028 1.0000
16.250 1.3870 0.06743 0.06306 -0.0262 0.0028 1.0000
16.500 1.3851 0.07114 0.06686 -0.0272 0.0027 1.0000
16.750 1.3805 0.07534 0.07117 -0.0284 0.0027 1.0000
17.000 1.3746 0.07987 0.07581 -0.0299 0.0027 1.0000
17.250 1.3693 0.08446 0.08050 -0.0315 0.0027 1.0000
17.500 1.3632 0.08930 0.08545 -0.0334 0.0027 1.0000
17.750 1.3524 0.09504 0.09132 -0.0358 0.0027 1.0000
18.000 1.3461 0.10017 0.09655 -0.0380 0.0026 1.0000
18.250 1.3368 0.10598 0.10247 -0.0407 0.0026 1.0000
18.500 1.3244 0.11249 0.10912 -0.0438 0.0026 1.0000
18.750 1.3162 0.11834 0.11507 -0.0468 0.0026 1.0000
19.000 1.3051 0.12490 0.12175 -0.0502 0.0026 1.0000
19.250 1.2953 0.13134 0.12830 -0.0538 0.0026 1.0000
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Polar data table (+)
Polar graphs
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