E230 (9.96%) (e230-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 50,000 Max Cl/Cd: 23.03 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e230-il-50000.txt Download as CSV file: xf-e230-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7498 0.11143 0.10501 0.0219 1.0000 0.1377
-10.250 -0.7918 0.09498 0.08862 0.0078 1.0000 0.1091
-10.000 -0.7902 0.08960 0.08326 0.0065 1.0000 0.1074
-9.750 -0.8034 0.08326 0.07692 0.0036 1.0000 0.1046
-9.500 -0.8877 0.07535 0.06854 0.0007 1.0000 0.0961
-9.250 -0.8817 0.07015 0.06330 0.0009 1.0000 0.0948
-9.000 -0.8864 0.06531 0.05826 0.0016 1.0000 0.0936
-8.750 -0.8915 0.06055 0.05318 0.0027 1.0000 0.0928
-8.500 -0.8932 0.05600 0.04822 0.0041 1.0000 0.0925
-8.250 -0.8906 0.05174 0.04347 0.0058 1.0000 0.0932
-8.000 -0.8838 0.04775 0.03891 0.0077 1.0000 0.0943
-7.750 -0.8735 0.04414 0.03460 0.0097 1.0000 0.0960
-7.500 -0.8534 0.04036 0.03072 0.0105 1.0000 0.0996
-7.250 -0.8318 0.03723 0.02726 0.0117 1.0000 0.1052
-7.000 -0.8098 0.03440 0.02424 0.0128 1.0000 0.1158
-6.750 -0.7870 0.03176 0.02140 0.0140 1.0000 0.1348
-6.500 -0.7683 0.02933 0.01927 0.0157 1.0000 0.1728
-6.250 -0.7568 0.02763 0.01795 0.0184 1.0000 0.2322
-6.000 -0.7432 0.02604 0.01669 0.0213 1.0000 0.2962
-5.750 -0.7271 0.02478 0.01579 0.0240 1.0000 0.3577
-5.500 -0.7099 0.02376 0.01505 0.0267 1.0000 0.4180
-5.250 -0.6913 0.02290 0.01440 0.0294 1.0000 0.4765
-5.000 -0.6716 0.02221 0.01389 0.0322 1.0000 0.5337
-4.750 -0.6509 0.02167 0.01350 0.0350 1.0000 0.5899
-4.500 -0.6258 0.02142 0.01339 0.0376 1.0000 0.6438
-4.250 -0.5992 0.02134 0.01331 0.0402 1.0000 0.6962
-4.000 -0.5632 0.02169 0.01360 0.0417 1.0000 0.7449
-3.750 -0.5169 0.02237 0.01408 0.0417 1.0000 0.7898
-3.500 -0.4599 0.02316 0.01454 0.0395 1.0000 0.8303
-3.250 -0.3837 0.02394 0.01490 0.0333 1.0000 0.8662
-3.000 -0.3197 0.02403 0.01465 0.0276 1.0000 0.9018
-2.750 -0.2456 0.02364 0.01397 0.0191 1.0000 0.9340
-2.500 -0.1744 0.02275 0.01282 0.0101 1.0000 0.9654
-2.250 -0.1002 0.02134 0.01121 -0.0004 1.0000 0.9956
-2.000 -0.0748 0.02042 0.01023 -0.0025 1.0000 1.0000
-1.750 -0.0583 0.01975 0.00954 -0.0027 1.0000 1.0000
-1.500 -0.0413 0.01919 0.00898 -0.0027 1.0000 1.0000
-1.250 -0.0239 0.01871 0.00851 -0.0027 1.0000 1.0000
-1.000 -0.0062 0.01833 0.00814 -0.0026 1.0000 1.0000
-0.750 0.0113 0.01803 0.00788 -0.0023 1.0000 1.0000
-0.500 0.0276 0.01781 0.00772 -0.0018 1.0000 1.0000
-0.250 0.0410 0.01771 0.00769 -0.0009 1.0000 1.0000
0.000 0.0466 0.01777 0.00781 0.0013 1.0000 1.0000
0.250 0.0408 0.01802 0.00808 0.0052 1.0000 1.0000
0.500 0.0309 0.01838 0.00843 0.0097 1.0000 1.0000
0.750 0.0222 0.01879 0.00882 0.0138 1.0000 1.0000
1.000 0.0167 0.01925 0.00924 0.0173 1.0000 1.0000
1.250 0.0143 0.01976 0.00973 0.0203 1.0000 1.0000
1.500 0.0965 0.02062 0.01083 0.0078 0.9748 1.0000
1.750 0.2080 0.02116 0.01175 -0.0088 0.9410 1.0000
2.000 0.3090 0.02114 0.01216 -0.0217 0.9029 1.0000
2.250 0.3504 0.02125 0.01246 -0.0230 0.8630 1.0000
2.500 0.3744 0.02140 0.01274 -0.0207 0.8267 1.0000
2.750 0.3899 0.02161 0.01302 -0.0170 0.7908 1.0000
3.000 0.4043 0.02173 0.01319 -0.0126 0.7570 1.0000
3.250 0.4177 0.02179 0.01327 -0.0080 0.7240 1.0000
3.500 0.4319 0.02195 0.01350 -0.0040 0.6870 1.0000
3.750 0.4463 0.02198 0.01351 0.0005 0.6516 1.0000
4.000 0.4620 0.02209 0.01362 0.0044 0.6117 1.0000
4.250 0.4783 0.02219 0.01366 0.0082 0.5704 1.0000
4.500 0.4954 0.02239 0.01377 0.0118 0.5250 1.0000
4.750 0.5132 0.02269 0.01396 0.0150 0.4758 1.0000
5.000 0.5313 0.02318 0.01425 0.0180 0.4228 1.0000
5.250 0.5496 0.02386 0.01463 0.0207 0.3680 1.0000
5.500 0.5681 0.02488 0.01544 0.0228 0.3111 1.0000
5.750 0.5864 0.02626 0.01663 0.0249 0.2558 1.0000
6.000 0.6029 0.02771 0.01778 0.0268 0.2009 1.0000
6.250 0.6200 0.02957 0.01942 0.0285 0.1581 1.0000
6.500 0.6395 0.03188 0.02162 0.0299 0.1342 1.0000
6.750 0.6595 0.03438 0.02426 0.0312 0.1205 1.0000
7.000 0.6784 0.03740 0.02779 0.0326 0.1138 1.0000
7.250 0.6972 0.04045 0.03082 0.0336 0.1084 1.0000
7.500 0.7084 0.04401 0.03512 0.0350 0.1057 1.0000
7.750 0.7161 0.04789 0.03954 0.0361 0.1035 1.0000
8.000 0.7195 0.05213 0.04422 0.0371 0.1027 1.0000
8.250 0.7176 0.05683 0.04930 0.0378 0.1039 1.0000
8.500 0.7119 0.06172 0.05445 0.0381 0.1054 1.0000
8.750 0.7077 0.06647 0.05933 0.0383 0.1070 1.0000
9.000 0.7137 0.07115 0.06405 0.0387 0.1086 1.0000
9.250 0.6311 0.08111 0.07413 0.0306 0.1180 1.0000
9.500 0.6192 0.08822 0.08120 0.0264 0.1242 1.0000
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Polar data table (+)
Polar graphs
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