E222 (10.17%) (e222-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.24 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e222-il-1000000.txt Download as CSV file: xf-e222-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3808 0.08188 0.08036 -0.0376 1.0000 0.0143
-10.000 -0.3868 0.07741 0.07590 -0.0383 1.0000 0.0146
-9.750 -0.3950 0.07251 0.07103 -0.0391 1.0000 0.0148
-9.500 -0.4086 0.06663 0.06517 -0.0404 1.0000 0.0149
-9.250 -0.4326 0.05868 0.05726 -0.0424 1.0000 0.0148
-8.000 -0.5422 0.02317 0.01958 -0.0781 0.9853 0.0122
-7.750 -0.5119 0.02059 0.01666 -0.0801 0.9842 0.0122
-7.500 -0.4866 0.01863 0.01445 -0.0805 0.9808 0.0122
-7.250 -0.4584 0.01703 0.01265 -0.0813 0.9778 0.0122
-7.000 -0.4273 0.01564 0.01108 -0.0825 0.9758 0.0123
-6.750 -0.3948 0.01447 0.00977 -0.0838 0.9742 0.0124
-6.500 -0.3607 0.01373 0.00893 -0.0854 0.9730 0.0127
-6.250 -0.3259 0.01301 0.00813 -0.0871 0.9720 0.0130
-6.000 -0.2910 0.01216 0.00720 -0.0888 0.9711 0.0132
-5.750 -0.2685 0.01081 0.00575 -0.0880 0.9647 0.0137
-5.500 -0.2362 0.01003 0.00490 -0.0892 0.9620 0.0143
-5.250 -0.2029 0.00948 0.00430 -0.0905 0.9596 0.0148
-5.000 -0.1715 0.00905 0.00382 -0.0913 0.9559 0.0153
-4.750 -0.1432 0.00867 0.00340 -0.0914 0.9494 0.0158
-4.500 -0.1102 0.00832 0.00299 -0.0925 0.9452 0.0165
-4.250 -0.0811 0.00804 0.00268 -0.0927 0.9377 0.0174
-4.000 -0.0494 0.00775 0.00232 -0.0934 0.9311 0.0188
-3.750 -0.0206 0.00750 0.00204 -0.0935 0.9218 0.0225
-3.500 0.0082 0.00701 0.00173 -0.0938 0.9126 0.0712
-3.250 0.0361 0.00660 0.00153 -0.0940 0.9021 0.1343
-3.000 0.0634 0.00631 0.00139 -0.0940 0.8907 0.1866
-2.750 0.0907 0.00603 0.00127 -0.0940 0.8792 0.2465
-2.500 0.1181 0.00582 0.00118 -0.0940 0.8674 0.2970
-2.250 0.1455 0.00568 0.00111 -0.0939 0.8552 0.3391
-2.000 0.1727 0.00555 0.00105 -0.0937 0.8423 0.3824
-1.750 0.1996 0.00538 0.00101 -0.0936 0.8289 0.4417
-1.500 0.2265 0.00525 0.00099 -0.0934 0.8149 0.4939
-1.250 0.2536 0.00520 0.00097 -0.0931 0.8007 0.5293
-1.000 0.2807 0.00516 0.00095 -0.0929 0.7861 0.5593
-0.750 0.3078 0.00514 0.00095 -0.0927 0.7713 0.5906
-0.500 0.3347 0.00512 0.00096 -0.0924 0.7561 0.6215
-0.250 0.3617 0.00512 0.00097 -0.0921 0.7405 0.6509
0.000 0.3885 0.00513 0.00099 -0.0919 0.7242 0.6788
0.250 0.4153 0.00514 0.00103 -0.0915 0.7074 0.7058
0.500 0.4419 0.00517 0.00107 -0.0912 0.6901 0.7319
0.750 0.4684 0.00521 0.00111 -0.0908 0.6728 0.7570
1.000 0.4948 0.00527 0.00116 -0.0904 0.6554 0.7815
1.250 0.5209 0.00533 0.00122 -0.0899 0.6374 0.8043
1.500 0.5470 0.00540 0.00129 -0.0895 0.6186 0.8267
1.750 0.5726 0.00548 0.00137 -0.0889 0.5989 0.8478
2.000 0.5977 0.00558 0.00145 -0.0882 0.5788 0.8694
2.250 0.6224 0.00567 0.00153 -0.0874 0.5585 0.8905
2.500 0.6459 0.00579 0.00162 -0.0863 0.5370 0.9123
2.750 0.6686 0.00588 0.00169 -0.0851 0.5159 0.9348
3.000 0.6915 0.00599 0.00176 -0.0839 0.4935 0.9624
3.250 0.7242 0.00615 0.00184 -0.0850 0.4672 1.0000
3.500 0.7508 0.00635 0.00196 -0.0849 0.4437 1.0000
3.750 0.7771 0.00659 0.00209 -0.0846 0.4183 1.0000
4.000 0.8032 0.00683 0.00223 -0.0844 0.3927 1.0000
4.250 0.8289 0.00711 0.00240 -0.0840 0.3644 1.0000
4.500 0.8539 0.00745 0.00259 -0.0836 0.3295 1.0000
4.750 0.8786 0.00782 0.00280 -0.0831 0.2937 1.0000
5.000 0.9029 0.00822 0.00304 -0.0826 0.2580 1.0000
5.250 0.9269 0.00865 0.00330 -0.0820 0.2214 1.0000
5.500 0.9508 0.00909 0.00357 -0.0815 0.1892 1.0000
5.750 0.9748 0.00952 0.00386 -0.0809 0.1598 1.0000
6.000 0.9983 0.00998 0.00419 -0.0803 0.1311 1.0000
6.250 1.0217 0.01045 0.00453 -0.0796 0.1051 1.0000
6.500 1.0447 0.01096 0.00490 -0.0789 0.0811 1.0000
6.750 1.0672 0.01150 0.00531 -0.0781 0.0585 1.0000
7.000 1.0888 0.01213 0.00579 -0.0772 0.0352 1.0000
7.250 1.1078 0.01302 0.00650 -0.0758 0.0120 1.0000
7.500 1.1307 0.01351 0.00700 -0.0750 0.0096 1.0000
7.750 1.1529 0.01406 0.00759 -0.0740 0.0083 1.0000
8.000 1.1750 0.01460 0.00819 -0.0731 0.0078 1.0000
8.250 1.1973 0.01508 0.00873 -0.0722 0.0075 1.0000
8.500 1.2188 0.01563 0.00934 -0.0712 0.0072 1.0000
8.750 1.2397 0.01621 0.00998 -0.0701 0.0070 1.0000
9.000 1.2598 0.01683 0.01066 -0.0689 0.0067 1.0000
9.250 1.2788 0.01751 0.01139 -0.0676 0.0064 1.0000
9.500 1.2965 0.01827 0.01222 -0.0660 0.0062 1.0000
9.750 1.3115 0.01919 0.01322 -0.0641 0.0060 1.0000
10.000 1.3200 0.02053 0.01469 -0.0612 0.0057 1.0000
10.250 1.3205 0.02211 0.01641 -0.0569 0.0055 1.0000
10.500 1.3314 0.02297 0.01735 -0.0544 0.0055 1.0000
10.750 1.3411 0.02393 0.01839 -0.0518 0.0054 1.0000
11.000 1.3497 0.02498 0.01954 -0.0492 0.0054 1.0000
11.250 1.3564 0.02620 0.02086 -0.0466 0.0053 1.0000
11.500 1.3619 0.02757 0.02233 -0.0440 0.0053 1.0000
11.750 1.3671 0.02901 0.02387 -0.0416 0.0052 1.0000
12.000 1.3733 0.03039 0.02535 -0.0395 0.0051 1.0000
12.250 1.3773 0.03203 0.02710 -0.0374 0.0050 1.0000
12.500 1.3789 0.03398 0.02917 -0.0354 0.0050 1.0000
12.750 1.3803 0.03604 0.03137 -0.0337 0.0049 1.0000
13.000 1.3811 0.03825 0.03370 -0.0322 0.0049 1.0000
13.250 1.3789 0.04092 0.03651 -0.0310 0.0049 1.0000
13.500 1.3760 0.04379 0.03952 -0.0300 0.0048 1.0000
13.750 1.3706 0.04715 0.04303 -0.0294 0.0048 1.0000
14.000 1.3656 0.05058 0.04661 -0.0293 0.0048 1.0000
14.250 1.3582 0.05456 0.05075 -0.0296 0.0048 1.0000
14.500 1.3503 0.05880 0.05513 -0.0304 0.0048 1.0000
14.750 1.3391 0.06380 0.06031 -0.0318 0.0048 1.0000
15.000 1.3277 0.06913 0.06580 -0.0337 0.0048 1.0000
15.250 1.3158 0.07486 0.07168 -0.0361 0.0048 1.0000
15.500 1.3008 0.08149 0.07849 -0.0393 0.0048 1.0000
15.750 1.2870 0.08828 0.08543 -0.0428 0.0048 1.0000
16.000 1.2701 0.09602 0.09333 -0.0471 0.0049 1.0000
16.250 1.2524 0.10437 0.10184 -0.0520 0.0049 1.0000
16.500 1.2340 0.11324 0.11087 -0.0573 0.0050 1.0000
16.750 1.2162 0.12235 0.12012 -0.0629 0.0050 1.0000
17.000 1.1970 0.13218 0.13010 -0.0690 0.0050 1.0000
17.250 1.1776 0.14245 0.14051 -0.0755 0.0051 1.0000
17.500 1.1561 0.15371 0.15191 -0.0826 0.0051 1.0000
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Polar data table (+)
Polar graphs
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