E201 (11.88%) (e201-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E201 (11.88%) (e201-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.9 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e201-il-1000000.txt Download as CSV file: xf-e201-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4372 0.08320 0.08163 -0.0454 1.0000 0.0150
-10.000 -0.4408 0.07931 0.07775 -0.0469 1.0000 0.0152
-9.750 -0.4646 0.07077 0.06926 -0.0508 1.0000 0.0152
-9.250 -0.6043 0.02611 0.02268 -0.0820 0.9852 0.0107
-9.000 -0.5829 0.02292 0.01919 -0.0835 0.9804 0.0109
-8.750 -0.5558 0.02100 0.01710 -0.0850 0.9757 0.0112
-8.500 -0.5262 0.01915 0.01504 -0.0865 0.9716 0.0114
-8.250 -0.5033 0.01776 0.01349 -0.0863 0.9611 0.0115
-8.000 -0.4765 0.01670 0.01230 -0.0866 0.9499 0.0118
-7.750 -0.4494 0.01567 0.01113 -0.0869 0.9347 0.0121
-7.250 -0.3998 0.01404 0.00915 -0.0861 0.8901 0.0125
-7.000 -0.3765 0.01341 0.00835 -0.0853 0.8674 0.0128
-6.750 -0.3533 0.01279 0.00758 -0.0845 0.8466 0.0130
-6.500 -0.3296 0.01226 0.00690 -0.0838 0.8277 0.0132
-6.250 -0.3056 0.01176 0.00625 -0.0831 0.8103 0.0134
-6.000 -0.2811 0.01130 0.00567 -0.0825 0.7945 0.0136
-5.750 -0.2558 0.01097 0.00523 -0.0821 0.7801 0.0139
-5.250 -0.2063 0.00993 0.00395 -0.0811 0.7541 0.0150
-5.000 -0.1804 0.00958 0.00351 -0.0807 0.7428 0.0157
-4.750 -0.1540 0.00933 0.00317 -0.0804 0.7325 0.0165
-4.500 -0.1273 0.00912 0.00288 -0.0802 0.7223 0.0174
-4.250 -0.1002 0.00893 0.00262 -0.0800 0.7130 0.0182
-4.000 -0.0733 0.00873 0.00235 -0.0798 0.7046 0.0201
-3.750 -0.0463 0.00849 0.00211 -0.0797 0.6961 0.0278
-3.500 -0.0204 0.00807 0.00188 -0.0795 0.6885 0.0770
-3.250 0.0063 0.00778 0.00172 -0.0794 0.6810 0.1192
-3.000 0.0331 0.00755 0.00160 -0.0793 0.6742 0.1608
-2.750 0.0601 0.00730 0.00149 -0.0792 0.6672 0.2071
-2.500 0.0869 0.00709 0.00139 -0.0792 0.6608 0.2566
-2.250 0.1138 0.00681 0.00132 -0.0791 0.6546 0.3221
-2.000 0.1405 0.00661 0.00127 -0.0790 0.6484 0.3864
-1.750 0.1681 0.00649 0.00125 -0.0790 0.6427 0.4291
-1.500 0.1958 0.00641 0.00123 -0.0790 0.6369 0.4613
-1.250 0.2232 0.00635 0.00122 -0.0789 0.6314 0.4946
-1.000 0.2512 0.00628 0.00121 -0.0789 0.6259 0.5211
-0.750 0.2789 0.00625 0.00120 -0.0789 0.6204 0.5425
-0.250 0.3346 0.00617 0.00121 -0.0789 0.6100 0.5902
0.000 0.3621 0.00615 0.00122 -0.0788 0.6047 0.6168
0.250 0.3897 0.00610 0.00125 -0.0788 0.5999 0.6458
0.500 0.4173 0.00604 0.00127 -0.0787 0.5946 0.6780
0.750 0.4442 0.00600 0.00131 -0.0785 0.5895 0.7148
1.000 0.4711 0.00593 0.00136 -0.0783 0.5846 0.7558
1.250 0.4975 0.00584 0.00140 -0.0779 0.5793 0.8011
1.500 0.5225 0.00578 0.00147 -0.0772 0.5740 0.8522
1.750 0.5463 0.00568 0.00153 -0.0760 0.5685 0.9123
2.000 0.5781 0.00568 0.00158 -0.0767 0.5618 0.9637
2.250 0.6183 0.00573 0.00162 -0.0794 0.5551 0.9860
2.500 0.6585 0.00579 0.00166 -0.0822 0.5478 0.9967
2.750 0.6894 0.00586 0.00170 -0.0829 0.5406 1.0000
3.000 0.7146 0.00593 0.00176 -0.0824 0.5329 1.0000
3.250 0.7400 0.00602 0.00182 -0.0819 0.5259 1.0000
3.500 0.7657 0.00610 0.00189 -0.0815 0.5180 1.0000
3.750 0.7916 0.00619 0.00196 -0.0811 0.5105 1.0000
4.000 0.8174 0.00630 0.00205 -0.0807 0.5014 1.0000
4.250 0.8437 0.00639 0.00214 -0.0804 0.4919 1.0000
4.500 0.8696 0.00651 0.00224 -0.0801 0.4822 1.0000
4.750 0.8955 0.00664 0.00235 -0.0798 0.4716 1.0000
5.000 0.9214 0.00678 0.00247 -0.0794 0.4582 1.0000
5.250 0.9460 0.00700 0.00260 -0.0789 0.4327 1.0000
5.500 0.9702 0.00726 0.00277 -0.0783 0.4072 1.0000
5.750 0.9932 0.00762 0.00300 -0.0775 0.3724 1.0000
6.000 1.0135 0.00819 0.00332 -0.0763 0.3208 1.0000
6.250 1.0324 0.00888 0.00373 -0.0749 0.2659 1.0000
6.500 1.0510 0.00957 0.00417 -0.0736 0.2159 1.0000
6.750 1.0699 0.01023 0.00462 -0.0722 0.1739 1.0000
7.000 1.0890 0.01086 0.00506 -0.0709 0.1388 1.0000
7.250 1.1073 0.01152 0.00553 -0.0695 0.1052 1.0000
7.500 1.1252 0.01218 0.00602 -0.0680 0.0771 1.0000
7.750 1.1423 0.01286 0.00656 -0.0664 0.0515 1.0000
8.000 1.1562 0.01371 0.00723 -0.0642 0.0252 1.0000
8.250 1.1703 0.01452 0.00794 -0.0621 0.0116 1.0000
8.500 1.1889 0.01500 0.00845 -0.0606 0.0102 1.0000
8.750 1.2061 0.01553 0.00901 -0.0590 0.0093 1.0000
9.000 1.2197 0.01611 0.00963 -0.0566 0.0085 1.0000
9.250 1.2307 0.01677 0.01037 -0.0539 0.0081 1.0000
9.500 1.2445 0.01731 0.01095 -0.0517 0.0079 1.0000
9.750 1.2569 0.01794 0.01164 -0.0494 0.0077 1.0000
10.000 1.2689 0.01861 0.01236 -0.0472 0.0074 1.0000
10.250 1.2791 0.01940 0.01323 -0.0448 0.0073 1.0000
10.500 1.2889 0.02025 0.01413 -0.0426 0.0070 1.0000
10.750 1.2975 0.02121 0.01515 -0.0403 0.0068 1.0000
11.000 1.3049 0.02229 0.01631 -0.0381 0.0066 1.0000
11.250 1.3119 0.02347 0.01756 -0.0361 0.0065 1.0000
11.500 1.3137 0.02509 0.01926 -0.0338 0.0062 1.0000
11.750 1.3191 0.02656 0.02080 -0.0321 0.0062 1.0000
12.000 1.3143 0.02892 0.02328 -0.0298 0.0060 1.0000
12.250 1.3084 0.03156 0.02604 -0.0279 0.0058 1.0000
12.500 1.3132 0.03340 0.02796 -0.0268 0.0057 1.0000
12.750 1.3181 0.03529 0.02992 -0.0259 0.0057 1.0000
13.000 1.3215 0.03738 0.03210 -0.0250 0.0057 1.0000
13.250 1.3250 0.03952 0.03432 -0.0243 0.0056 1.0000
13.500 1.3288 0.04169 0.03659 -0.0237 0.0055 1.0000
13.750 1.3304 0.04414 0.03913 -0.0232 0.0055 1.0000
14.000 1.3318 0.04668 0.04177 -0.0227 0.0055 1.0000
14.250 1.3340 0.04921 0.04439 -0.0225 0.0054 1.0000
14.500 1.3320 0.05229 0.04757 -0.0222 0.0054 1.0000
14.750 1.3344 0.05497 0.05034 -0.0223 0.0054 1.0000
15.000 1.3327 0.05820 0.05368 -0.0224 0.0054 1.0000
15.250 1.3320 0.06142 0.05701 -0.0227 0.0053 1.0000
15.500 1.3322 0.06464 0.06033 -0.0233 0.0053 1.0000
15.750 1.3295 0.06832 0.06412 -0.0239 0.0052 1.0000
16.000 1.3262 0.07220 0.06812 -0.0247 0.0052 1.0000
16.250 1.3223 0.07629 0.07234 -0.0258 0.0052 1.0000
16.500 1.3175 0.08067 0.07684 -0.0271 0.0051 1.0000
16.750 1.3111 0.08539 0.08169 -0.0287 0.0052 1.0000
17.000 1.3047 0.09028 0.08673 -0.0305 0.0051 1.0000
17.250 1.2967 0.09562 0.09220 -0.0327 0.0051 1.0000
17.500 1.2880 0.10125 0.09796 -0.0352 0.0051 1.0000
17.750 1.2767 0.10746 0.10432 -0.0381 0.0051 1.0000
18.000 1.2699 0.11305 0.11003 -0.0410 0.0050 1.0000
18.250 1.2590 0.11961 0.11673 -0.0445 0.0050 1.0000
18.500 1.2420 0.12756 0.12485 -0.0488 0.0051 1.0000
18.750 1.2321 0.13430 0.13171 -0.0528 0.0050 1.0000
19.000 1.2144 0.14294 0.14052 -0.0579 0.0051 1.0000
19.250 1.2004 0.15105 0.14877 -0.0629 0.0051 1.0000
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Polar data table (+)
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