E222 (10.17%) (e222-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 500,000 Max Cl/Cd: 89.8 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e222-il-500000-n5.txt Download as CSV file: xf-e222-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5004 0.08714 0.08480 -0.0369 1.0000 0.0096
-10.250 -0.5232 0.07857 0.07628 -0.0404 1.0000 0.0095
-10.000 -0.6152 0.05255 0.05017 -0.0563 1.0000 0.0090
-9.750 -0.6489 0.04665 0.04419 -0.0598 1.0000 0.0089
-9.500 -0.6747 0.04254 0.03991 -0.0596 0.9998 0.0088
-9.250 -0.6648 0.03568 0.03253 -0.0669 0.9950 0.0090
-9.000 -0.6487 0.03128 0.02768 -0.0701 0.9910 0.0091
-8.750 -0.6270 0.02803 0.02404 -0.0723 0.9874 0.0092
-8.500 -0.6005 0.02560 0.02126 -0.0743 0.9850 0.0095
-8.250 -0.5707 0.02400 0.01938 -0.0762 0.9833 0.0098
-8.000 -0.5478 0.02248 0.01762 -0.0763 0.9786 0.0100
-7.750 -0.5200 0.02093 0.01582 -0.0773 0.9754 0.0101
-7.500 -0.4899 0.01960 0.01428 -0.0785 0.9730 0.0102
-7.000 -0.4359 0.01650 0.01080 -0.0797 0.9659 0.0106
-6.750 -0.4076 0.01526 0.00944 -0.0804 0.9623 0.0110
-6.500 -0.3763 0.01440 0.00850 -0.0815 0.9597 0.0113
-6.250 -0.3436 0.01366 0.00768 -0.0829 0.9578 0.0117
-6.000 -0.3179 0.01305 0.00701 -0.0827 0.9516 0.0120
-5.750 -0.2865 0.01245 0.00635 -0.0837 0.9478 0.0124
-5.500 -0.2531 0.01188 0.00570 -0.0850 0.9448 0.0128
-5.250 -0.2241 0.01141 0.00518 -0.0854 0.9387 0.0133
-5.000 -0.1919 0.01099 0.00470 -0.0864 0.9337 0.0140
-4.750 -0.1583 0.01058 0.00422 -0.0877 0.9292 0.0145
-4.500 -0.1283 0.01023 0.00379 -0.0882 0.9216 0.0148
-4.250 -0.0950 0.00983 0.00331 -0.0894 0.9155 0.0158
-4.000 -0.0653 0.00954 0.00297 -0.0898 0.9064 0.0171
-3.750 -0.0345 0.00929 0.00267 -0.0903 0.8976 0.0192
-3.500 -0.0043 0.00902 0.00239 -0.0908 0.8878 0.0279
-3.250 0.0237 0.00861 0.00214 -0.0910 0.8766 0.0738
-3.000 0.0517 0.00824 0.00194 -0.0912 0.8651 0.1266
-2.750 0.0797 0.00798 0.00178 -0.0913 0.8532 0.1705
-2.500 0.1072 0.00771 0.00165 -0.0914 0.8407 0.2250
-2.250 0.1346 0.00749 0.00155 -0.0914 0.8276 0.2766
-2.000 0.1617 0.00728 0.00147 -0.0913 0.8143 0.3326
-1.750 0.1886 0.00708 0.00141 -0.0912 0.8004 0.3953
-1.500 0.2156 0.00695 0.00137 -0.0910 0.7862 0.4429
-1.250 0.2426 0.00689 0.00134 -0.0908 0.7717 0.4756
-1.000 0.2696 0.00684 0.00131 -0.0906 0.7566 0.5087
-0.750 0.2964 0.00681 0.00130 -0.0903 0.7411 0.5402
-0.500 0.3232 0.00679 0.00131 -0.0900 0.7252 0.5704
-0.250 0.3498 0.00679 0.00132 -0.0897 0.7089 0.5998
0.000 0.3764 0.00679 0.00134 -0.0893 0.6923 0.6292
0.250 0.4028 0.00681 0.00138 -0.0889 0.6755 0.6576
0.500 0.4290 0.00685 0.00142 -0.0885 0.6582 0.6847
0.750 0.4552 0.00690 0.00147 -0.0881 0.6403 0.7106
1.000 0.4811 0.00696 0.00153 -0.0876 0.6215 0.7354
1.250 0.5068 0.00703 0.00161 -0.0870 0.6027 0.7600
1.500 0.5322 0.00712 0.00169 -0.0864 0.5840 0.7850
1.750 0.5573 0.00719 0.00178 -0.0857 0.5649 0.8095
2.000 0.5820 0.00730 0.00188 -0.0849 0.5449 0.8327
2.250 0.6063 0.00741 0.00199 -0.0841 0.5248 0.8551
2.500 0.6298 0.00754 0.00209 -0.0830 0.5034 0.8773
2.750 0.6527 0.00768 0.00220 -0.0819 0.4819 0.9008
3.000 0.6749 0.00780 0.00230 -0.0805 0.4597 0.9263
3.500 0.7314 0.00817 0.00253 -0.0808 0.4099 1.0000
3.750 0.7570 0.00843 0.00269 -0.0804 0.3848 1.0000
4.000 0.7823 0.00872 0.00287 -0.0800 0.3579 1.0000
4.250 0.8077 0.00901 0.00308 -0.0797 0.3336 1.0000
4.500 0.8327 0.00933 0.00330 -0.0793 0.3077 1.0000
4.750 0.8575 0.00968 0.00353 -0.0788 0.2810 1.0000
5.000 0.8810 0.01013 0.00381 -0.0782 0.2431 1.0000
5.250 0.9035 0.01070 0.00416 -0.0775 0.1993 1.0000
5.500 0.9269 0.01119 0.00449 -0.0768 0.1673 1.0000
5.750 0.9503 0.01165 0.00484 -0.0762 0.1409 1.0000
6.000 0.9733 0.01216 0.00521 -0.0755 0.1143 1.0000
6.250 0.9961 0.01269 0.00561 -0.0748 0.0903 1.0000
6.500 1.0185 0.01323 0.00606 -0.0740 0.0683 1.0000
6.750 1.0401 0.01385 0.00654 -0.0732 0.0465 1.0000
7.000 1.0619 0.01443 0.00704 -0.0723 0.0319 1.0000
7.250 1.0826 0.01512 0.00764 -0.0712 0.0158 1.0000
7.500 1.1036 0.01577 0.00826 -0.0702 0.0099 1.0000
7.750 1.1255 0.01630 0.00885 -0.0693 0.0085 1.0000
8.000 1.1473 0.01682 0.00944 -0.0683 0.0078 1.0000
8.250 1.1682 0.01741 0.01008 -0.0673 0.0071 1.0000
8.500 1.1880 0.01808 0.01082 -0.0661 0.0064 1.0000
8.750 1.2063 0.01887 0.01170 -0.0647 0.0059 1.0000
9.000 1.2253 0.01952 0.01243 -0.0634 0.0058 1.0000
9.250 1.2433 0.02023 0.01323 -0.0619 0.0056 1.0000
9.500 1.2601 0.02099 0.01409 -0.0604 0.0055 1.0000
9.750 1.2746 0.02179 0.01499 -0.0584 0.0053 1.0000
10.000 1.2871 0.02264 0.01592 -0.0561 0.0051 1.0000
10.250 1.2982 0.02355 0.01693 -0.0537 0.0050 1.0000
10.500 1.3082 0.02454 0.01802 -0.0512 0.0049 1.0000
10.750 1.3170 0.02561 0.01918 -0.0488 0.0048 1.0000
11.000 1.3246 0.02678 0.02046 -0.0463 0.0046 1.0000
11.250 1.3313 0.02805 0.02183 -0.0439 0.0045 1.0000
11.500 1.3366 0.02946 0.02337 -0.0416 0.0045 1.0000
11.750 1.3409 0.03100 0.02502 -0.0394 0.0044 1.0000
12.000 1.3445 0.03267 0.02681 -0.0374 0.0043 1.0000
12.250 1.3466 0.03456 0.02881 -0.0355 0.0042 1.0000
12.500 1.3477 0.03664 0.03102 -0.0339 0.0042 1.0000
12.750 1.3471 0.03900 0.03350 -0.0325 0.0041 1.0000
13.000 1.3462 0.04155 0.03619 -0.0315 0.0041 1.0000
13.250 1.3437 0.04441 0.03918 -0.0308 0.0040 1.0000
13.500 1.3400 0.04759 0.04250 -0.0304 0.0040 1.0000
13.750 1.3354 0.05104 0.04610 -0.0304 0.0040 1.0000
14.000 1.3298 0.05484 0.05004 -0.0308 0.0039 1.0000
14.250 1.3216 0.05919 0.05454 -0.0317 0.0039 1.0000
14.500 1.3126 0.06391 0.05942 -0.0331 0.0038 1.0000
14.750 1.3033 0.06896 0.06463 -0.0348 0.0038 1.0000
15.000 1.2916 0.07464 0.07048 -0.0371 0.0038 1.0000
15.250 1.2804 0.08057 0.07657 -0.0398 0.0038 1.0000
15.500 1.2684 0.08693 0.08309 -0.0430 0.0038 1.0000
15.750 1.2537 0.09407 0.09041 -0.0467 0.0037 1.0000
16.000 1.2400 0.10135 0.09784 -0.0507 0.0037 1.0000
16.250 1.2279 0.10859 0.10523 -0.0548 0.0037 1.0000
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Polar data table (+)
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