E222 (10.17%) (e222-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 50,000 Max Cl/Cd: 36.53 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e222-il-50000.txt Download as CSV file: xf-e222-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4035 0.10639 0.09940 -0.0208 1.0000 0.2635
-8.500 -0.3945 0.10244 0.09549 -0.0202 1.0000 0.2697
-8.250 -0.4153 0.10191 0.09512 -0.0202 1.0000 0.2795
-8.000 -0.3908 0.09684 0.08999 -0.0188 1.0000 0.2894
-7.750 -0.3908 0.09405 0.08729 -0.0179 1.0000 0.2995
-7.500 -0.4197 0.09388 0.08733 -0.0168 1.0000 0.3091
-7.250 -0.3976 0.08936 0.08279 -0.0154 1.0000 0.3213
-7.000 -0.3952 0.08619 0.07970 -0.0140 1.0000 0.3289
-6.500 -0.4994 0.06173 0.05510 -0.0463 1.0000 0.1353
-6.250 -0.4970 0.05459 0.04738 -0.0495 1.0000 0.1206
-6.000 -0.4839 0.05079 0.04357 -0.0486 1.0000 0.1178
-5.750 -0.4712 0.04638 0.03883 -0.0491 1.0000 0.1150
-5.500 -0.4552 0.04223 0.03419 -0.0498 1.0000 0.1142
-5.250 -0.4357 0.03865 0.03008 -0.0502 1.0000 0.1153
-5.000 -0.4135 0.03543 0.02631 -0.0503 1.0000 0.1165
-4.750 -0.3893 0.03259 0.02287 -0.0502 1.0000 0.1182
-4.500 -0.3646 0.03011 0.01996 -0.0497 1.0000 0.1221
-4.250 -0.3411 0.02832 0.01804 -0.0489 1.0000 0.1314
-4.000 -0.3169 0.02669 0.01620 -0.0481 1.0000 0.1487
-3.750 -0.2932 0.02488 0.01465 -0.0471 1.0000 0.1806
-3.500 -0.2710 0.02316 0.01360 -0.0464 1.0000 0.2850
-3.250 -0.2523 0.02212 0.01329 -0.0445 1.0000 0.4157
-3.000 -0.2357 0.02161 0.01319 -0.0416 1.0000 0.5166
-2.750 -0.2225 0.02134 0.01325 -0.0376 1.0000 0.5970
-2.500 -0.2119 0.02113 0.01325 -0.0330 1.0000 0.6700
-2.250 -0.2048 0.02095 0.01319 -0.0277 1.0000 0.7389
-2.000 -0.2030 0.02070 0.01309 -0.0213 1.0000 0.8055
-1.750 -0.1999 0.02027 0.01279 -0.0150 1.0000 0.8904
-1.500 -0.1392 0.01964 0.01177 -0.0235 1.0000 1.0000
-1.250 -0.1126 0.01960 0.01127 -0.0265 1.0000 1.0000
-1.000 -0.0868 0.01982 0.01113 -0.0282 1.0000 1.0000
-0.750 -0.0628 0.02014 0.01115 -0.0293 1.0000 1.0000
-0.500 -0.0400 0.02054 0.01129 -0.0300 1.0000 1.0000
-0.250 -0.0182 0.02099 0.01150 -0.0305 1.0000 1.0000
0.000 0.0030 0.02150 0.01182 -0.0308 1.0000 1.0000
0.250 0.0236 0.02207 0.01221 -0.0312 1.0000 1.0000
0.500 0.0436 0.02269 0.01269 -0.0314 1.0000 1.0000
0.750 0.0631 0.02337 0.01324 -0.0317 1.0000 1.0000
1.000 0.0822 0.02410 0.01386 -0.0320 1.0000 1.0000
1.250 0.1184 0.02526 0.01491 -0.0355 0.9917 1.0000
1.500 0.1692 0.02662 0.01619 -0.0414 0.9749 1.0000
1.750 0.2199 0.02789 0.01739 -0.0471 0.9583 1.0000
2.000 0.2629 0.02887 0.01834 -0.0512 0.9405 1.0000
2.250 0.3057 0.02978 0.01925 -0.0551 0.9223 1.0000
2.500 0.3506 0.03064 0.02013 -0.0590 0.9046 1.0000
2.750 0.3988 0.03140 0.02094 -0.0632 0.8871 1.0000
3.000 0.4326 0.03206 0.02167 -0.0649 0.8674 1.0000
3.250 0.4736 0.03261 0.02230 -0.0675 0.8481 1.0000
3.500 0.5212 0.03295 0.02279 -0.0706 0.8300 1.0000
3.750 0.5561 0.03338 0.02334 -0.0718 0.8096 1.0000
4.000 0.5981 0.03351 0.02363 -0.0736 0.7897 1.0000
4.250 0.6542 0.03296 0.02333 -0.0765 0.7715 1.0000
4.500 0.6888 0.03301 0.02355 -0.0767 0.7494 1.0000
4.750 0.7409 0.03209 0.02287 -0.0782 0.7295 1.0000
5.000 0.7803 0.03156 0.02259 -0.0780 0.7066 1.0000
5.250 0.8333 0.03011 0.02137 -0.0786 0.6839 1.0000
5.500 0.8688 0.02950 0.02093 -0.0775 0.6565 1.0000
5.750 0.9063 0.02871 0.02032 -0.0763 0.6269 1.0000
6.000 0.9412 0.02809 0.01977 -0.0748 0.5946 1.0000
6.250 0.9662 0.02806 0.01982 -0.0725 0.5585 1.0000
6.500 0.9946 0.02787 0.01962 -0.0704 0.5199 1.0000
6.750 1.0197 0.02797 0.01960 -0.0681 0.4788 1.0000
7.000 1.0396 0.02846 0.01998 -0.0655 0.4356 1.0000
7.250 1.0584 0.02918 0.02051 -0.0629 0.3913 1.0000
7.500 1.0744 0.03019 0.02134 -0.0602 0.3471 1.0000
7.750 1.0902 0.03145 0.02241 -0.0577 0.3044 1.0000
8.000 1.1033 0.03304 0.02392 -0.0550 0.2650 1.0000
8.250 1.1182 0.03492 0.02565 -0.0527 0.2288 1.0000
8.500 1.1314 0.03696 0.02759 -0.0503 0.1953 1.0000
8.750 1.1435 0.03904 0.02943 -0.0480 0.1639 1.0000
9.000 1.1520 0.04129 0.03165 -0.0454 0.1375 1.0000
9.250 1.1635 0.04421 0.03464 -0.0433 0.1179 1.0000
9.500 1.1771 0.04751 0.03815 -0.0415 0.1050 1.0000
9.750 1.1929 0.05092 0.04173 -0.0401 0.0965 1.0000
10.000 1.1964 0.05486 0.04615 -0.0376 0.0922 1.0000
10.250 1.1941 0.05857 0.05037 -0.0348 0.0888 1.0000
10.500 1.1937 0.06227 0.05438 -0.0325 0.0862 1.0000
10.750 1.1922 0.06627 0.05864 -0.0305 0.0846 1.0000
11.000 1.1743 0.07035 0.06310 -0.0275 0.0849 1.0000
11.250 1.1448 0.07462 0.06772 -0.0247 0.0859 1.0000
11.500 1.1119 0.07969 0.07308 -0.0237 0.0875 1.0000
11.750 1.0790 0.08584 0.07945 -0.0248 0.0895 1.0000
12.000 1.0498 0.09285 0.08660 -0.0276 0.0914 1.0000
12.250 1.0261 0.10041 0.09423 -0.0312 0.0932 1.0000
12.500 1.0082 0.10817 0.10204 -0.0351 0.0943 1.0000
12.750 0.8643 0.15459 0.14802 -0.0741 0.2093 1.0000
13.000 0.8735 0.15766 0.15111 -0.0733 0.1871 1.0000
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Polar data table (+)
Polar graphs
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