E226 (10.19%) (e226-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 50,000 Max Cl/Cd: 32.2 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e226-il-50000-n5.txt Download as CSV file: xf-e226-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5882 0.09754 0.09039 -0.0176 1.0000 0.0431
-10.250 -0.5951 0.09103 0.08394 -0.0213 1.0000 0.0426
-10.000 -0.6057 0.08369 0.07664 -0.0260 1.0000 0.0418
-9.750 -0.6229 0.07597 0.06893 -0.0319 1.0000 0.0409
-9.500 -0.6457 0.06931 0.06222 -0.0367 1.0000 0.0401
-9.250 -0.6674 0.06442 0.05722 -0.0380 1.0000 0.0394
-9.000 -0.6824 0.05988 0.05247 -0.0384 1.0000 0.0392
-8.750 -0.6897 0.05587 0.04819 -0.0381 1.0000 0.0395
-8.500 -0.6918 0.05215 0.04415 -0.0373 1.0000 0.0402
-8.250 -0.6894 0.04865 0.04029 -0.0363 1.0000 0.0410
-8.000 -0.6829 0.04532 0.03655 -0.0352 1.0000 0.0418
-7.750 -0.6729 0.04217 0.03295 -0.0338 1.0000 0.0428
-7.500 -0.6592 0.03929 0.02964 -0.0325 1.0000 0.0436
-7.250 -0.6425 0.03669 0.02660 -0.0311 1.0000 0.0446
-7.000 -0.6242 0.03439 0.02401 -0.0297 1.0000 0.0460
-6.750 -0.6062 0.03249 0.02203 -0.0284 1.0000 0.0480
-6.500 -0.5880 0.03087 0.02028 -0.0270 1.0000 0.0515
-6.250 -0.5690 0.02935 0.01851 -0.0253 1.0000 0.0570
-6.000 -0.5524 0.02790 0.01709 -0.0238 1.0000 0.0634
-5.750 -0.5355 0.02641 0.01554 -0.0220 1.0000 0.0723
-5.500 -0.5193 0.02491 0.01405 -0.0203 1.0000 0.0922
-5.250 -0.5036 0.02341 0.01290 -0.0189 1.0000 0.1375
-5.000 -0.4884 0.02216 0.01212 -0.0176 1.0000 0.2118
-4.750 -0.4717 0.02124 0.01143 -0.0160 1.0000 0.2735
-4.500 -0.4543 0.02053 0.01088 -0.0145 1.0000 0.3306
-4.250 -0.4370 0.01995 0.01039 -0.0127 1.0000 0.3843
-4.000 -0.4199 0.01945 0.01001 -0.0107 1.0000 0.4342
-3.750 -0.4026 0.01904 0.00970 -0.0086 1.0000 0.4834
-3.500 -0.3852 0.01869 0.00944 -0.0065 1.0000 0.5322
-3.250 -0.3679 0.01840 0.00920 -0.0043 1.0000 0.5800
-3.000 -0.3506 0.01817 0.00906 -0.0020 1.0000 0.6270
-2.750 -0.3334 0.01800 0.00895 0.0005 1.0000 0.6732
-2.500 -0.3160 0.01789 0.00889 0.0029 1.0000 0.7196
-2.250 -0.2976 0.01783 0.00885 0.0053 1.0000 0.7666
-2.000 -0.2759 0.01784 0.00886 0.0070 1.0000 0.8152
-1.750 -0.2463 0.01791 0.00888 0.0070 1.0000 0.8659
-1.500 -0.2019 0.01805 0.00887 0.0039 1.0000 0.9149
-1.250 -0.1384 0.01823 0.00884 -0.0033 0.9955 0.9559
-1.000 -0.0697 0.01833 0.00872 -0.0120 0.9897 0.9881
-0.750 -0.0193 0.01841 0.00862 -0.0176 0.9785 1.0000
-0.500 0.0221 0.01849 0.00856 -0.0214 0.9640 1.0000
-0.250 0.0635 0.01858 0.00853 -0.0250 0.9497 1.0000
0.000 0.1053 0.01865 0.00852 -0.0284 0.9357 1.0000
0.250 0.1475 0.01870 0.00851 -0.0317 0.9216 1.0000
0.500 0.1867 0.01873 0.00850 -0.0342 0.9065 1.0000
0.750 0.2231 0.01875 0.00851 -0.0360 0.8906 1.0000
1.000 0.2573 0.01877 0.00853 -0.0373 0.8740 1.0000
1.250 0.2896 0.01879 0.00855 -0.0380 0.8570 1.0000
1.500 0.3205 0.01880 0.00858 -0.0383 0.8397 1.0000
1.750 0.3480 0.01884 0.00864 -0.0380 0.8212 1.0000
2.000 0.3728 0.01892 0.00874 -0.0371 0.8013 1.0000
2.250 0.3985 0.01897 0.00881 -0.0362 0.7820 1.0000
2.500 0.4246 0.01900 0.00889 -0.0352 0.7631 1.0000
2.750 0.4466 0.01914 0.00905 -0.0337 0.7412 1.0000
3.000 0.4709 0.01921 0.00915 -0.0324 0.7203 1.0000
3.250 0.4937 0.01934 0.00932 -0.0310 0.6977 1.0000
3.500 0.5176 0.01945 0.00948 -0.0296 0.6750 1.0000
3.750 0.5402 0.01962 0.00969 -0.0281 0.6501 1.0000
4.000 0.5634 0.01978 0.00988 -0.0266 0.6250 1.0000
4.250 0.5865 0.01997 0.01011 -0.0251 0.5988 1.0000
4.500 0.6086 0.02022 0.01039 -0.0235 0.5704 1.0000
4.750 0.6306 0.02050 0.01069 -0.0220 0.5407 1.0000
5.000 0.6523 0.02082 0.01102 -0.0204 0.5099 1.0000
5.250 0.6732 0.02121 0.01144 -0.0188 0.4767 1.0000
5.500 0.6936 0.02165 0.01189 -0.0172 0.4420 1.0000
5.750 0.7135 0.02216 0.01236 -0.0156 0.4069 1.0000
6.000 0.7327 0.02276 0.01295 -0.0140 0.3698 1.0000
6.250 0.7511 0.02346 0.01361 -0.0124 0.3328 1.0000
6.500 0.7688 0.02426 0.01438 -0.0108 0.2946 1.0000
6.750 0.7854 0.02519 0.01521 -0.0092 0.2580 1.0000
7.000 0.8016 0.02625 0.01622 -0.0077 0.2212 1.0000
7.250 0.8165 0.02747 0.01734 -0.0061 0.1880 1.0000
7.500 0.8307 0.02887 0.01864 -0.0045 0.1567 1.0000
7.750 0.8434 0.03042 0.02016 -0.0029 0.1257 1.0000
8.000 0.8540 0.03203 0.02165 -0.0014 0.0965 1.0000
8.250 0.8641 0.03385 0.02334 0.0002 0.0769 1.0000
8.500 0.8754 0.03576 0.02527 0.0018 0.0648 1.0000
8.750 0.8877 0.03772 0.02734 0.0034 0.0565 1.0000
9.000 0.9024 0.03993 0.02974 0.0049 0.0514 1.0000
9.250 0.9163 0.04204 0.03206 0.0063 0.0473 1.0000
9.500 0.9274 0.04423 0.03424 0.0075 0.0441 1.0000
9.750 0.9394 0.04684 0.03729 0.0089 0.0415 1.0000
10.000 0.9475 0.04962 0.04041 0.0103 0.0395 1.0000
10.250 0.9516 0.05250 0.04358 0.0118 0.0386 1.0000
10.500 0.9511 0.05555 0.04690 0.0134 0.0378 1.0000
10.750 0.9466 0.05885 0.05044 0.0146 0.0372 1.0000
11.000 0.9386 0.06246 0.05431 0.0152 0.0369 1.0000
11.250 0.9264 0.06662 0.05871 0.0150 0.0368 1.0000
11.500 0.9104 0.07146 0.06378 0.0136 0.0367 1.0000
11.750 0.8893 0.07753 0.07008 0.0107 0.0370 1.0000
12.000 0.8634 0.08526 0.07802 0.0058 0.0375 1.0000
12.250 0.8298 0.09605 0.08899 -0.0018 0.0386 1.0000
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Polar data table (+)
Polar graphs
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