E222 (10.17%) (e222-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 50,000 Max Cl/Cd: 38.83 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e222-il-50000-n5.txt Download as CSV file: xf-e222-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4605 0.08991 0.08279 -0.0434 1.0000 0.0482
-9.000 -0.4633 0.08595 0.07891 -0.0442 1.0000 0.0479
-8.750 -0.4689 0.08176 0.07480 -0.0453 1.0000 0.0475
-8.500 -0.4797 0.07702 0.07015 -0.0471 1.0000 0.0471
-8.250 -0.4926 0.07248 0.06569 -0.0491 1.0000 0.0466
-8.000 -0.5052 0.06784 0.06105 -0.0508 1.0000 0.0462
-7.750 -0.5152 0.06343 0.05658 -0.0518 1.0000 0.0458
-7.500 -0.5225 0.05906 0.05207 -0.0524 1.0000 0.0455
-7.250 -0.5256 0.05476 0.04755 -0.0528 1.0000 0.0452
-7.000 -0.5243 0.05057 0.04305 -0.0529 1.0000 0.0451
-6.750 -0.5182 0.04660 0.03868 -0.0528 1.0000 0.0451
-6.500 -0.5077 0.04297 0.03461 -0.0526 1.0000 0.0453
-6.250 -0.4936 0.03969 0.03086 -0.0522 1.0000 0.0457
-6.000 -0.4766 0.03682 0.02750 -0.0516 1.0000 0.0464
-5.750 -0.4575 0.03442 0.02460 -0.0509 1.0000 0.0478
-5.500 -0.4385 0.03241 0.02239 -0.0502 1.0000 0.0502
-5.250 -0.4189 0.03092 0.02077 -0.0495 1.0000 0.0536
-5.000 -0.3980 0.02940 0.01896 -0.0485 1.0000 0.0567
-4.750 -0.3766 0.02797 0.01725 -0.0473 1.0000 0.0595
-4.500 -0.3558 0.02665 0.01583 -0.0462 1.0000 0.0633
-4.250 -0.3346 0.02555 0.01464 -0.0454 1.0000 0.0694
-4.000 -0.3125 0.02446 0.01351 -0.0448 1.0000 0.0822
-3.750 -0.2896 0.02325 0.01243 -0.0445 1.0000 0.1150
-3.500 -0.2660 0.02200 0.01174 -0.0451 1.0000 0.2071
-3.250 -0.2434 0.02123 0.01144 -0.0451 1.0000 0.3123
-3.000 -0.2220 0.02079 0.01127 -0.0444 1.0000 0.3934
-2.750 -0.2015 0.02052 0.01117 -0.0433 1.0000 0.4639
-2.500 -0.1821 0.02035 0.01113 -0.0419 1.0000 0.5264
-2.250 -0.1494 0.02033 0.01120 -0.0427 0.9922 0.5984
-2.000 -0.1175 0.02038 0.01132 -0.0431 0.9838 0.6664
-1.750 -0.0893 0.02039 0.01138 -0.0427 0.9743 0.7292
-1.500 -0.0623 0.02038 0.01138 -0.0419 0.9647 0.7914
-1.250 -0.0317 0.02036 0.01134 -0.0417 0.9558 0.8611
-1.000 0.0162 0.02023 0.01110 -0.0455 0.9472 0.9522
-0.750 0.0597 0.02024 0.01082 -0.0495 0.9365 1.0000
-0.500 0.0990 0.02041 0.01073 -0.0525 0.9271 1.0000
-0.250 0.1378 0.02057 0.01068 -0.0553 0.9171 1.0000
0.000 0.1723 0.02071 0.01064 -0.0571 0.9057 1.0000
0.250 0.2080 0.02086 0.01064 -0.0590 0.8948 1.0000
0.500 0.2469 0.02097 0.01063 -0.0613 0.8850 1.0000
0.750 0.2839 0.02106 0.01062 -0.0632 0.8743 1.0000
1.000 0.3176 0.02117 0.01066 -0.0645 0.8622 1.0000
1.250 0.3523 0.02125 0.01070 -0.0658 0.8505 1.0000
1.500 0.3877 0.02131 0.01072 -0.0672 0.8389 1.0000
1.750 0.4240 0.02131 0.01071 -0.0685 0.8276 1.0000
2.000 0.4599 0.02129 0.01072 -0.0697 0.8158 1.0000
2.250 0.4919 0.02133 0.01077 -0.0702 0.8020 1.0000
2.500 0.5239 0.02136 0.01082 -0.0706 0.7880 1.0000
2.750 0.5560 0.02137 0.01089 -0.0710 0.7735 1.0000
3.000 0.5880 0.02136 0.01094 -0.0713 0.7585 1.0000
3.250 0.6185 0.02140 0.01102 -0.0713 0.7423 1.0000
3.500 0.6465 0.02149 0.01119 -0.0709 0.7244 1.0000
3.750 0.6758 0.02155 0.01135 -0.0706 0.7063 1.0000
4.000 0.7062 0.02157 0.01143 -0.0704 0.6879 1.0000
4.250 0.7339 0.02169 0.01161 -0.0698 0.6676 1.0000
4.500 0.7612 0.02181 0.01181 -0.0691 0.6462 1.0000
4.750 0.7881 0.02197 0.01208 -0.0684 0.6238 1.0000
5.000 0.8148 0.02215 0.01231 -0.0676 0.6003 1.0000
5.250 0.8389 0.02242 0.01265 -0.0664 0.5747 1.0000
5.500 0.8629 0.02272 0.01300 -0.0653 0.5479 1.0000
5.750 0.8861 0.02306 0.01343 -0.0640 0.5198 1.0000
6.000 0.9082 0.02346 0.01386 -0.0626 0.4903 1.0000
6.250 0.9293 0.02393 0.01435 -0.0611 0.4595 1.0000
6.500 0.9492 0.02448 0.01489 -0.0595 0.4277 1.0000
6.750 0.9677 0.02512 0.01552 -0.0578 0.3947 1.0000
7.000 0.9849 0.02586 0.01631 -0.0560 0.3610 1.0000
7.250 1.0010 0.02670 0.01711 -0.0541 0.3276 1.0000
7.500 1.0160 0.02765 0.01803 -0.0522 0.2948 1.0000
7.750 1.0297 0.02873 0.01908 -0.0502 0.2620 1.0000
8.000 1.0425 0.02993 0.02024 -0.0483 0.2315 1.0000
8.250 1.0542 0.03125 0.02153 -0.0463 0.2032 1.0000
8.500 1.0648 0.03271 0.02300 -0.0443 0.1772 1.0000
8.750 1.0738 0.03431 0.02453 -0.0422 0.1545 1.0000
9.000 1.0814 0.03599 0.02625 -0.0399 0.1329 1.0000
9.250 1.0860 0.03787 0.02804 -0.0376 0.1143 1.0000
9.500 1.0895 0.03982 0.03005 -0.0354 0.0952 1.0000
9.750 1.0902 0.04191 0.03212 -0.0333 0.0794 1.0000
10.000 1.0922 0.04423 0.03447 -0.0315 0.0672 1.0000
10.250 1.0955 0.04675 0.03711 -0.0298 0.0583 1.0000
10.500 1.0966 0.04939 0.03972 -0.0284 0.0529 1.0000
10.750 1.1037 0.05204 0.04268 -0.0271 0.0472 1.0000
11.000 1.1050 0.05477 0.04548 -0.0261 0.0435 1.0000
11.250 1.1090 0.05777 0.04870 -0.0252 0.0408 1.0000
11.500 1.1139 0.06111 0.05241 -0.0243 0.0386 1.0000
11.750 1.1150 0.06475 0.05635 -0.0237 0.0372 1.0000
12.000 1.1124 0.06869 0.06058 -0.0235 0.0362 1.0000
12.250 1.1062 0.07307 0.06523 -0.0239 0.0355 1.0000
12.500 1.0969 0.07792 0.07034 -0.0249 0.0350 1.0000
12.750 1.0844 0.08342 0.07610 -0.0267 0.0347 1.0000
13.000 1.0684 0.08975 0.08268 -0.0294 0.0347 1.0000
13.250 1.0484 0.09727 0.09045 -0.0335 0.0349 1.0000
13.500 1.0243 0.10638 0.09979 -0.0390 0.0354 1.0000
13.750 0.9967 0.11744 0.11106 -0.0461 0.0362 1.0000
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Polar data table (+)
Polar graphs
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