E222 (10.17%) (e222-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E222 (10.17%) (e222-il) Reynolds number: 100,000 Max Cl/Cd: 56.53 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e222-il-100000.txt Download as CSV file: xf-e222-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4179 0.09276 0.08789 -0.0317 1.0000 0.1284
-8.250 -0.4467 0.09047 0.08578 -0.0347 1.0000 0.1337
-8.000 -0.4836 0.08700 0.08252 -0.0385 1.0000 0.1351
-7.750 -0.4420 0.08384 0.07925 -0.0318 1.0000 0.1387
-7.500 -0.4464 0.08147 0.07695 -0.0302 1.0000 0.1427
-7.250 -0.5004 0.07668 0.07230 -0.0401 1.0000 0.1493
-7.000 -0.4805 0.07416 0.06986 -0.0340 1.0000 0.1514
-6.750 -0.4741 0.07202 0.06775 -0.0310 1.0000 0.1560
-6.500 -0.4949 0.06708 0.06278 -0.0362 1.0000 0.1649
-6.250 -0.5074 0.04289 0.03653 -0.0504 1.0000 0.0660
-6.000 -0.4935 0.03837 0.03190 -0.0502 1.0000 0.0643
-5.750 -0.4763 0.03501 0.02811 -0.0499 1.0000 0.0640
-5.500 -0.4564 0.03201 0.02465 -0.0496 1.0000 0.0637
-5.250 -0.4344 0.02921 0.02141 -0.0492 1.0000 0.0629
-5.000 -0.4108 0.02687 0.01865 -0.0488 1.0000 0.0625
-4.750 -0.3864 0.02502 0.01645 -0.0482 1.0000 0.0630
-4.500 -0.3620 0.02351 0.01464 -0.0475 1.0000 0.0645
-4.250 -0.3380 0.02218 0.01314 -0.0467 1.0000 0.0666
-4.000 -0.3155 0.02098 0.01205 -0.0462 1.0000 0.0730
-3.750 -0.2923 0.02002 0.01105 -0.0455 1.0000 0.0812
-3.500 -0.2685 0.01893 0.01010 -0.0451 1.0000 0.0975
-3.250 -0.2412 0.01692 0.00901 -0.0459 1.0000 0.2412
-3.000 -0.2190 0.01643 0.00902 -0.0457 1.0000 0.3587
-2.750 -0.1984 0.01624 0.00919 -0.0450 1.0000 0.4565
-2.500 -0.1794 0.01615 0.00940 -0.0436 1.0000 0.5352
-2.250 -0.1614 0.01616 0.00958 -0.0419 1.0000 0.6016
-2.000 -0.1425 0.01624 0.00983 -0.0403 0.9991 0.6657
-1.750 -0.1070 0.01654 0.01027 -0.0414 0.9901 0.7381
-1.500 -0.0750 0.01680 0.01061 -0.0416 0.9809 0.8058
-1.250 -0.0449 0.01696 0.01085 -0.0411 0.9714 0.8790
-1.000 0.0079 0.01678 0.01062 -0.0459 0.9616 1.0000
-0.750 0.0546 0.01699 0.01054 -0.0509 0.9521 1.0000
-0.500 0.1052 0.01723 0.01057 -0.0561 0.9443 1.0000
-0.250 0.1449 0.01736 0.01054 -0.0590 0.9329 1.0000
0.000 0.1856 0.01750 0.01053 -0.0619 0.9222 1.0000
0.250 0.2325 0.01758 0.01050 -0.0658 0.9139 1.0000
0.500 0.2741 0.01759 0.01043 -0.0686 0.9033 1.0000
0.750 0.3124 0.01760 0.01038 -0.0706 0.8918 1.0000
1.000 0.3554 0.01750 0.01024 -0.0733 0.8819 1.0000
1.250 0.4048 0.01723 0.00995 -0.0770 0.8739 1.0000
1.500 0.4431 0.01708 0.00979 -0.0787 0.8621 1.0000
1.750 0.4826 0.01686 0.00958 -0.0804 0.8508 1.0000
2.000 0.5260 0.01650 0.00924 -0.0826 0.8408 1.0000
2.250 0.5666 0.01615 0.00891 -0.0841 0.8293 1.0000
2.500 0.6013 0.01593 0.00873 -0.0847 0.8151 1.0000
2.750 0.6355 0.01570 0.00852 -0.0851 0.8002 1.0000
3.000 0.6661 0.01558 0.00842 -0.0849 0.7831 1.0000
3.250 0.6947 0.01552 0.00838 -0.0843 0.7644 1.0000
3.500 0.7249 0.01543 0.00832 -0.0840 0.7456 1.0000
3.750 0.7559 0.01535 0.00821 -0.0837 0.7268 1.0000
4.000 0.7808 0.01545 0.00833 -0.0826 0.7037 1.0000
4.250 0.8088 0.01548 0.00836 -0.0819 0.6815 1.0000
4.500 0.8340 0.01561 0.00848 -0.0808 0.6566 1.0000
4.750 0.8585 0.01577 0.00863 -0.0796 0.6304 1.0000
5.000 0.8828 0.01596 0.00880 -0.0784 0.6032 1.0000
5.250 0.9063 0.01620 0.00902 -0.0770 0.5744 1.0000
5.500 0.9289 0.01648 0.00927 -0.0756 0.5439 1.0000
5.750 0.9508 0.01682 0.00954 -0.0741 0.5119 1.0000
6.000 0.9720 0.01722 0.00985 -0.0725 0.4789 1.0000
6.250 0.9914 0.01768 0.01030 -0.0708 0.4424 1.0000
6.500 1.0103 0.01823 0.01072 -0.0689 0.4058 1.0000
6.750 1.0277 0.01886 0.01128 -0.0670 0.3661 1.0000
7.000 1.0441 0.01961 0.01191 -0.0650 0.3255 1.0000
7.250 1.0594 0.02051 0.01265 -0.0629 0.2855 1.0000
7.500 1.0736 0.02159 0.01353 -0.0608 0.2470 1.0000
7.750 1.0873 0.02274 0.01457 -0.0586 0.2089 1.0000
8.000 1.0989 0.02397 0.01561 -0.0563 0.1738 1.0000
8.250 1.1093 0.02509 0.01661 -0.0541 0.1387 1.0000
8.500 1.1178 0.02666 0.01799 -0.0516 0.1089 1.0000
8.750 1.1235 0.02872 0.01986 -0.0487 0.0811 1.0000
9.000 1.1324 0.03096 0.02209 -0.0459 0.0634 1.0000
9.250 1.1477 0.03346 0.02453 -0.0443 0.0553 1.0000
9.500 1.1648 0.03540 0.02658 -0.0429 0.0494 1.0000
9.750 1.1859 0.03821 0.02946 -0.0423 0.0451 1.0000
10.000 1.2055 0.04076 0.03231 -0.0412 0.0426 1.0000
10.250 1.2235 0.04369 0.03553 -0.0400 0.0410 1.0000
10.500 1.2367 0.04677 0.03893 -0.0385 0.0400 1.0000
10.750 1.2445 0.05008 0.04257 -0.0365 0.0395 1.0000
11.000 1.2458 0.05349 0.04635 -0.0340 0.0394 1.0000
11.250 1.2375 0.05693 0.05018 -0.0306 0.0395 1.0000
11.500 1.2224 0.06054 0.05418 -0.0273 0.0399 1.0000
11.750 1.2033 0.06449 0.05848 -0.0246 0.0403 1.0000
12.000 1.1813 0.06892 0.06324 -0.0230 0.0407 1.0000
12.250 1.1576 0.07388 0.06849 -0.0227 0.0412 1.0000
12.500 1.1319 0.07955 0.07441 -0.0238 0.0417 1.0000
12.750 1.1051 0.08602 0.08111 -0.0263 0.0422 1.0000
13.000 1.0770 0.09355 0.08885 -0.0305 0.0427 1.0000
13.250 1.0473 0.10248 0.09794 -0.0363 0.0434 1.0000
13.500 1.0175 0.11292 0.10849 -0.0435 0.0442 1.0000
13.750 0.9917 0.12405 0.11966 -0.0508 0.0452 1.0000
14.000 0.9778 0.13316 0.12877 -0.0557 0.0462 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E222 (10.17%) (e222-il)