E10(08%) (e228-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 200,000 Max Cl/Cd: 48.2 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e228-il-200000-n5.txt Download as CSV file: xf-e228-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7837 0.08871 0.08529 0.0008 1.0000 0.0107
-12.000 -0.8212 0.07459 0.07104 -0.0092 1.0000 0.0100
-11.750 -0.8501 0.06441 0.06065 -0.0173 1.0000 0.0097
-11.500 -0.8732 0.05725 0.05328 -0.0225 1.0000 0.0096
-11.250 -0.8928 0.05198 0.04779 -0.0251 1.0000 0.0095
-11.000 -0.9083 0.04812 0.04370 -0.0254 1.0000 0.0096
-10.750 -0.9235 0.04466 0.03999 -0.0240 1.0000 0.0096
-10.500 -0.9332 0.04194 0.03702 -0.0215 1.0000 0.0098
-10.250 -0.9348 0.03959 0.03441 -0.0193 1.0000 0.0102
-10.000 -0.9325 0.03701 0.03151 -0.0174 1.0000 0.0107
-9.750 -0.9242 0.03500 0.02917 -0.0157 1.0000 0.0115
-9.500 -0.9129 0.03309 0.02691 -0.0141 1.0000 0.0121
-9.250 -0.9019 0.03059 0.02408 -0.0125 1.0000 0.0125
-9.000 -0.8892 0.02821 0.02147 -0.0111 1.0000 0.0132
-8.750 -0.8725 0.02664 0.01977 -0.0099 1.0000 0.0138
-8.500 -0.8543 0.02526 0.01825 -0.0089 1.0000 0.0147
-8.250 -0.8352 0.02395 0.01678 -0.0078 1.0000 0.0156
-8.000 -0.8146 0.02295 0.01561 -0.0069 1.0000 0.0171
-7.750 -0.7939 0.02192 0.01443 -0.0059 1.0000 0.0185
-7.500 -0.7764 0.02044 0.01288 -0.0046 1.0000 0.0200
-7.250 -0.7561 0.01947 0.01180 -0.0035 1.0000 0.0213
-7.000 -0.7347 0.01870 0.01095 -0.0026 1.0000 0.0233
-6.750 -0.7129 0.01801 0.01015 -0.0017 1.0000 0.0255
-6.500 -0.6926 0.01713 0.00917 -0.0005 1.0000 0.0272
-6.250 -0.6722 0.01633 0.00831 0.0007 1.0000 0.0300
-6.000 -0.6507 0.01572 0.00764 0.0018 1.0000 0.0335
-5.750 -0.6300 0.01511 0.00699 0.0030 1.0000 0.0399
-5.500 -0.6106 0.01446 0.00640 0.0044 1.0000 0.0554
-5.250 -0.5923 0.01385 0.00591 0.0059 1.0000 0.0808
-5.000 -0.5740 0.01336 0.00552 0.0075 1.0000 0.1068
-4.750 -0.5427 0.01287 0.00513 0.0063 0.9929 0.1400
-4.500 -0.5089 0.01232 0.00477 0.0046 0.9847 0.1843
-4.250 -0.4769 0.01174 0.00448 0.0032 0.9755 0.2469
-4.000 -0.4439 0.01130 0.00419 0.0018 0.9668 0.2979
-3.750 -0.4117 0.01094 0.00396 0.0007 0.9572 0.3414
-3.500 -0.3813 0.01062 0.00377 0.0001 0.9464 0.3838
-3.250 -0.3520 0.01033 0.00359 -0.0003 0.9354 0.4246
-3.000 -0.3239 0.01008 0.00342 -0.0003 0.9238 0.4633
-2.750 -0.2972 0.00986 0.00329 0.0001 0.9118 0.5008
-2.500 -0.2716 0.00965 0.00317 0.0008 0.8994 0.5373
-2.250 -0.2468 0.00946 0.00307 0.0017 0.8865 0.5733
-2.000 -0.2225 0.00928 0.00297 0.0027 0.8732 0.6088
-1.750 -0.1981 0.00913 0.00289 0.0038 0.8598 0.6443
-1.500 -0.1736 0.00898 0.00283 0.0049 0.8461 0.6789
-1.250 -0.1488 0.00886 0.00278 0.0059 0.8323 0.7128
-1.000 -0.1236 0.00876 0.00274 0.0069 0.8182 0.7454
-0.750 -0.0978 0.00869 0.00271 0.0077 0.8038 0.7761
-0.500 -0.0711 0.00864 0.00270 0.0084 0.7892 0.8050
-0.250 -0.0432 0.00863 0.00269 0.0089 0.7740 0.8317
0.000 -0.0140 0.00865 0.00270 0.0091 0.7583 0.8563
0.250 0.0179 0.00869 0.00272 0.0086 0.7413 0.8771
0.500 0.0505 0.00875 0.00275 0.0080 0.7235 0.8959
0.750 0.0839 0.00883 0.00278 0.0072 0.7050 0.9120
1.000 0.1184 0.00893 0.00281 0.0060 0.6854 0.9256
1.250 0.1537 0.00904 0.00286 0.0047 0.6643 0.9370
1.500 0.1884 0.00915 0.00291 0.0035 0.6425 0.9474
1.750 0.2220 0.00928 0.00296 0.0024 0.6194 0.9574
2.000 0.2570 0.00942 0.00303 0.0010 0.5948 0.9660
2.250 0.2925 0.00955 0.00309 -0.0006 0.5686 0.9736
2.500 0.3264 0.00971 0.00317 -0.0018 0.5413 0.9819
2.750 0.3637 0.00986 0.00322 -0.0039 0.5107 0.9878
3.000 0.3993 0.01004 0.00332 -0.0057 0.4788 0.9942
3.250 0.4361 0.01022 0.00341 -0.0078 0.4446 0.9996
3.500 0.4597 0.01042 0.00352 -0.0071 0.4144 1.0000
3.750 0.4822 0.01066 0.00366 -0.0062 0.3837 1.0000
4.000 0.5047 0.01092 0.00386 -0.0054 0.3527 1.0000
4.250 0.5271 0.01122 0.00406 -0.0045 0.3217 1.0000
4.500 0.5495 0.01154 0.00429 -0.0036 0.2889 1.0000
4.750 0.5716 0.01192 0.00456 -0.0028 0.2556 1.0000
5.000 0.5936 0.01233 0.00486 -0.0019 0.2229 1.0000
5.250 0.6155 0.01277 0.00519 -0.0010 0.1904 1.0000
5.500 0.6371 0.01325 0.00561 -0.0001 0.1605 1.0000
5.750 0.6586 0.01376 0.00602 0.0009 0.1333 1.0000
6.000 0.6800 0.01428 0.00648 0.0018 0.1107 1.0000
6.250 0.7011 0.01485 0.00698 0.0028 0.0906 1.0000
6.500 0.7222 0.01542 0.00753 0.0038 0.0755 1.0000
6.750 0.7430 0.01602 0.00812 0.0049 0.0614 1.0000
7.000 0.7635 0.01666 0.00876 0.0059 0.0481 1.0000
7.250 0.7836 0.01731 0.00939 0.0070 0.0367 1.0000
7.500 0.8028 0.01810 0.01015 0.0082 0.0287 1.0000
7.750 0.8226 0.01881 0.01098 0.0094 0.0235 1.0000
8.000 0.8397 0.01986 0.01208 0.0110 0.0193 1.0000
8.250 0.8579 0.02073 0.01307 0.0123 0.0164 1.0000
8.500 0.8737 0.02186 0.01424 0.0138 0.0142 1.0000
8.750 0.8913 0.02276 0.01532 0.0152 0.0127 1.0000
9.000 0.9068 0.02390 0.01660 0.0167 0.0117 1.0000
9.250 0.9215 0.02508 0.01791 0.0183 0.0110 1.0000
9.500 0.9351 0.02633 0.01928 0.0199 0.0104 1.0000
9.750 0.9468 0.02775 0.02082 0.0216 0.0100 1.0000
10.000 0.9556 0.02944 0.02265 0.0236 0.0096 1.0000
10.250 0.9612 0.03153 0.02491 0.0257 0.0093 1.0000
10.500 0.9679 0.03329 0.02687 0.0277 0.0092 1.0000
10.750 0.9695 0.03520 0.02900 0.0303 0.0090 1.0000
11.000 0.9689 0.03726 0.03127 0.0325 0.0089 1.0000
11.250 0.9651 0.03976 0.03400 0.0343 0.0088 1.0000
11.500 0.9602 0.04246 0.03693 0.0354 0.0087 1.0000
11.750 0.9528 0.04563 0.04033 0.0357 0.0086 1.0000
12.000 0.9442 0.04920 0.04410 0.0352 0.0086 1.0000
12.250 0.9323 0.05354 0.04868 0.0336 0.0083 1.0000
12.500 0.9198 0.05841 0.05376 0.0312 0.0084 1.0000
12.750 0.9054 0.06410 0.05965 0.0278 0.0084 1.0000
13.000 0.8870 0.07112 0.06686 0.0231 0.0084 1.0000
13.250 0.8692 0.07866 0.07457 0.0180 0.0083 1.0000
13.500 0.8480 0.08723 0.08325 0.0126 0.0088 1.0000
13.750 0.8215 0.09800 0.09416 0.0058 0.0088 1.0000
14.000 0.7981 0.10841 0.10465 -0.0001 0.0091 1.0000
14.250 0.7696 0.12096 0.11726 -0.0067 0.0093 1.0000
14.500 0.7413 0.13443 0.13076 -0.0130 0.0095 1.0000
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Polar data table (+)
Polar graphs
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