E226 (10.19%) (e226-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 50,000 Max Cl/Cd: 30.45 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e226-il-50000.txt Download as CSV file: xf-e226-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5216 0.09994 0.09310 -0.0007 1.0000 0.2868
-8.500 -0.6131 0.07524 0.06859 -0.0301 1.0000 0.1246
-8.250 -0.6498 0.06689 0.05994 -0.0346 1.0000 0.1125
-8.000 -0.6467 0.06233 0.05530 -0.0345 1.0000 0.1108
-7.750 -0.6481 0.05756 0.05033 -0.0344 1.0000 0.1091
-7.500 -0.6480 0.05287 0.04531 -0.0340 1.0000 0.1070
-7.250 -0.6453 0.04836 0.04037 -0.0330 1.0000 0.1056
-7.000 -0.6378 0.04424 0.03576 -0.0317 1.0000 0.1046
-6.750 -0.6262 0.04055 0.03158 -0.0301 1.0000 0.1045
-6.500 -0.6109 0.03737 0.02798 -0.0285 1.0000 0.1059
-6.250 -0.5931 0.03453 0.02470 -0.0269 1.0000 0.1088
-6.000 -0.5742 0.03195 0.02175 -0.0253 1.0000 0.1156
-5.750 -0.5540 0.02991 0.01941 -0.0236 1.0000 0.1273
-5.500 -0.5328 0.02763 0.01731 -0.0221 1.0000 0.1455
-5.250 -0.5151 0.02561 0.01550 -0.0201 1.0000 0.1864
-5.000 -0.5040 0.02411 0.01454 -0.0173 1.0000 0.2609
-4.750 -0.4917 0.02283 0.01373 -0.0142 1.0000 0.3425
-4.500 -0.4779 0.02191 0.01319 -0.0109 1.0000 0.4159
-4.250 -0.4634 0.02123 0.01279 -0.0075 1.0000 0.4836
-4.000 -0.4485 0.02070 0.01250 -0.0040 1.0000 0.5476
-3.750 -0.4340 0.02030 0.01228 -0.0001 1.0000 0.6078
-3.500 -0.4203 0.02002 0.01214 0.0042 1.0000 0.6648
-3.250 -0.4073 0.01983 0.01201 0.0088 1.0000 0.7203
-3.000 -0.3941 0.01974 0.01196 0.0136 1.0000 0.7751
-2.750 -0.3742 0.01979 0.01200 0.0176 1.0000 0.8318
-2.500 -0.3193 0.02024 0.01216 0.0155 1.0000 0.8979
-2.250 -0.1452 0.02062 0.01164 -0.0093 1.0000 0.9610
-2.000 -0.0291 0.01952 0.01003 -0.0278 1.0000 1.0000
-1.750 -0.0398 0.01906 0.00958 -0.0241 1.0000 1.0000
-1.500 -0.0561 0.01870 0.00923 -0.0193 1.0000 1.0000
-1.250 -0.0736 0.01843 0.00894 -0.0140 1.0000 1.0000
-1.000 -0.0851 0.01828 0.00869 -0.0093 1.0000 1.0000
-0.750 -0.0877 0.01827 0.00855 -0.0058 1.0000 1.0000
-0.500 -0.0838 0.01837 0.00852 -0.0032 1.0000 1.0000
-0.250 -0.0753 0.01857 0.00859 -0.0014 1.0000 1.0000
0.000 -0.0641 0.01885 0.00875 0.0001 1.0000 1.0000
0.250 -0.0513 0.01919 0.00899 0.0012 1.0000 1.0000
0.500 -0.0377 0.01960 0.00930 0.0021 1.0000 1.0000
0.750 -0.0234 0.02007 0.00969 0.0028 1.0000 1.0000
1.000 -0.0088 0.02060 0.01015 0.0034 1.0000 1.0000
1.250 0.0142 0.02131 0.01083 0.0022 0.9966 1.0000
1.500 0.0749 0.02259 0.01211 -0.0058 0.9764 1.0000
1.750 0.1350 0.02373 0.01329 -0.0133 0.9560 1.0000
2.000 0.1870 0.02460 0.01424 -0.0190 0.9336 1.0000
2.250 0.2464 0.02540 0.01515 -0.0256 0.9123 1.0000
2.500 0.2926 0.02598 0.01587 -0.0294 0.8886 1.0000
2.750 0.3496 0.02639 0.01645 -0.0346 0.8657 1.0000
3.000 0.4046 0.02655 0.01683 -0.0390 0.8417 1.0000
3.250 0.4497 0.02664 0.01712 -0.0411 0.8169 1.0000
3.500 0.5032 0.02625 0.01697 -0.0436 0.7934 1.0000
3.750 0.5366 0.02617 0.01707 -0.0429 0.7668 1.0000
4.000 0.5681 0.02600 0.01706 -0.0417 0.7395 1.0000
4.250 0.5985 0.02574 0.01694 -0.0399 0.7116 1.0000
4.500 0.6268 0.02546 0.01681 -0.0376 0.6824 1.0000
4.750 0.6534 0.02519 0.01662 -0.0350 0.6513 1.0000
5.000 0.6794 0.02491 0.01639 -0.0322 0.6185 1.0000
5.250 0.7023 0.02485 0.01635 -0.0293 0.5823 1.0000
5.500 0.7257 0.02479 0.01627 -0.0264 0.5436 1.0000
5.750 0.7464 0.02500 0.01643 -0.0235 0.5012 1.0000
6.000 0.7668 0.02533 0.01663 -0.0207 0.4564 1.0000
6.250 0.7867 0.02584 0.01690 -0.0180 0.4094 1.0000
6.500 0.8035 0.02671 0.01769 -0.0153 0.3605 1.0000
6.750 0.8204 0.02778 0.01856 -0.0129 0.3128 1.0000
7.000 0.8371 0.02913 0.01968 -0.0105 0.2673 1.0000
7.250 0.8530 0.03082 0.02117 -0.0083 0.2244 1.0000
7.500 0.8663 0.03259 0.02275 -0.0059 0.1836 1.0000
7.750 0.8799 0.03456 0.02442 -0.0039 0.1483 1.0000
8.000 0.8961 0.03706 0.02703 -0.0021 0.1255 1.0000
8.250 0.9141 0.03991 0.03004 -0.0007 0.1120 1.0000
8.500 0.9302 0.04351 0.03400 0.0008 0.1053 1.0000
8.750 0.9425 0.04680 0.03770 0.0025 0.1000 1.0000
9.000 0.9575 0.05030 0.04122 0.0034 0.0949 1.0000
9.250 0.9576 0.05422 0.04576 0.0056 0.0934 1.0000
9.500 0.9554 0.05846 0.05046 0.0074 0.0929 1.0000
9.750 0.9489 0.06297 0.05533 0.0089 0.0932 1.0000
10.000 0.9391 0.06750 0.06014 0.0102 0.0937 1.0000
10.250 0.9271 0.07211 0.06495 0.0111 0.0944 1.0000
10.500 0.9143 0.07674 0.06970 0.0119 0.0951 1.0000
10.750 0.8214 0.08693 0.08018 0.0048 0.1037 1.0000
11.000 0.8037 0.09458 0.08781 0.0005 0.1067 1.0000
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Polar data table (+)
Polar graphs
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