E231 (e231-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 50,000 Max Cl/Cd: 32.64 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e231-il-50000.txt Download as CSV file: xf-e231-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3724 0.10580 0.09962 -0.0298 1.0000 0.2725
-8.750 -0.4088 0.10619 0.10020 -0.0274 1.0000 0.2784
-8.500 -0.4036 0.10331 0.09736 -0.0245 1.0000 0.2918
-8.250 -0.4085 0.10118 0.09531 -0.0214 1.0000 0.3058
-8.000 -0.4124 0.09908 0.09328 -0.0184 1.0000 0.3195
-7.750 -0.4200 0.09712 0.09141 -0.0152 1.0000 0.3338
-7.500 -0.4364 0.09578 0.09017 -0.0116 1.0000 0.3498
-7.250 -0.4571 0.09464 0.08915 -0.0076 1.0000 0.3654
-5.000 -0.5914 0.05487 0.04751 -0.0108 1.0000 0.1190
-4.750 -0.5782 0.05096 0.04294 -0.0089 1.0000 0.1056
-4.500 -0.5639 0.04772 0.03944 -0.0073 1.0000 0.1031
-4.250 -0.5483 0.04477 0.03606 -0.0056 1.0000 0.1017
-4.000 -0.5303 0.04198 0.03276 -0.0038 1.0000 0.0995
-3.750 -0.5099 0.03951 0.02974 -0.0022 1.0000 0.0969
-3.500 -0.4877 0.03715 0.02688 -0.0005 1.0000 0.0965
-3.250 -0.4651 0.03526 0.02466 0.0008 1.0000 0.0981
-3.000 -0.1977 0.02855 0.02143 -0.0287 1.0000 1.0000
-2.750 -0.1937 0.02835 0.02081 -0.0258 1.0000 1.0000
-2.500 -0.1886 0.02821 0.02033 -0.0231 1.0000 1.0000
-2.250 -0.1826 0.02813 0.01990 -0.0204 1.0000 1.0000
-2.000 -0.1758 0.02810 0.01957 -0.0178 1.0000 1.0000
-1.750 -0.1685 0.02810 0.01930 -0.0153 1.0000 1.0000
-1.500 -0.1606 0.02814 0.01909 -0.0128 1.0000 1.0000
-1.250 -0.1523 0.02822 0.01894 -0.0105 1.0000 1.0000
-1.000 -0.1434 0.02833 0.01883 -0.0082 1.0000 1.0000
-0.750 -0.1342 0.02848 0.01873 -0.0060 1.0000 1.0000
-0.500 -0.1245 0.02866 0.01872 -0.0039 1.0000 1.0000
-0.250 -0.1144 0.02887 0.01875 -0.0019 1.0000 1.0000
0.000 -0.1039 0.02912 0.01883 0.0000 1.0000 1.0000
0.250 -0.0930 0.02941 0.01896 0.0018 1.0000 1.0000
0.500 -0.0818 0.02975 0.01915 0.0035 1.0000 1.0000
0.750 -0.0703 0.03012 0.01936 0.0051 1.0000 1.0000
1.000 -0.0585 0.03054 0.01965 0.0066 1.0000 1.0000
1.250 -0.0464 0.03101 0.02000 0.0080 1.0000 1.0000
1.500 -0.0340 0.03153 0.02042 0.0092 1.0000 1.0000
1.750 -0.0213 0.03210 0.02090 0.0103 1.0000 1.0000
2.000 -0.0085 0.03273 0.02143 0.0114 1.0000 1.0000
2.250 0.0045 0.03341 0.02204 0.0123 1.0000 1.0000
2.500 0.0176 0.03415 0.02272 0.0130 1.0000 1.0000
2.750 0.1021 0.03749 0.02599 0.0000 0.9629 1.0000
3.000 0.1512 0.03936 0.02785 -0.0056 0.9392 1.0000
3.250 0.1899 0.04078 0.02927 -0.0090 0.9183 1.0000
3.500 0.2277 0.04213 0.03064 -0.0121 0.8968 1.0000
3.750 0.2623 0.04332 0.03184 -0.0143 0.8761 1.0000
4.000 0.2987 0.04451 0.03308 -0.0167 0.8555 1.0000
4.250 0.3268 0.04544 0.03409 -0.0176 0.8352 1.0000
4.500 0.3715 0.04654 0.03527 -0.0208 0.8155 1.0000
4.750 0.3897 0.04724 0.03603 -0.0200 0.7947 1.0000
5.000 0.4270 0.04798 0.03687 -0.0217 0.7750 1.0000
5.250 0.4543 0.04862 0.03765 -0.0219 0.7549 1.0000
5.500 0.4847 0.04912 0.03827 -0.0223 0.7347 1.0000
5.750 0.5250 0.04931 0.03862 -0.0236 0.7155 1.0000
6.000 0.5460 0.04971 0.03918 -0.0226 0.6940 1.0000
6.250 0.5954 0.04912 0.03882 -0.0241 0.6753 1.0000
6.500 0.6121 0.04946 0.03928 -0.0223 0.6528 1.0000
6.750 0.6653 0.04795 0.03810 -0.0232 0.6338 1.0000
7.000 0.6865 0.04784 0.03815 -0.0214 0.6109 1.0000
7.250 0.7558 0.04414 0.03487 -0.0219 0.5920 1.0000
7.500 0.8059 0.04113 0.03222 -0.0207 0.5690 1.0000
7.750 0.9359 0.03327 0.02497 -0.0261 0.5285 1.0000
8.000 0.9977 0.03097 0.02259 -0.0271 0.4756 1.0000
8.250 1.0202 0.03126 0.02271 -0.0247 0.4312 1.0000
8.500 1.0396 0.03205 0.02327 -0.0223 0.3893 1.0000
8.750 1.0514 0.03323 0.02432 -0.0193 0.3531 1.0000
9.000 1.0687 0.03455 0.02547 -0.0172 0.3182 1.0000
9.250 1.0806 0.03607 0.02691 -0.0146 0.2886 1.0000
9.500 1.0953 0.03777 0.02852 -0.0125 0.2609 1.0000
9.750 1.1084 0.03951 0.03021 -0.0102 0.2365 1.0000
10.000 1.1178 0.04156 0.03237 -0.0077 0.2165 1.0000
10.250 1.1269 0.04352 0.03440 -0.0051 0.1979 1.0000
10.500 1.1486 0.04606 0.03681 -0.0043 0.1787 1.0000
10.750 1.1536 0.04829 0.03919 -0.0015 0.1645 1.0000
11.000 1.1512 0.05091 0.04219 0.0022 0.1552 1.0000
11.250 1.1481 0.05372 0.04526 0.0056 0.1466 1.0000
11.500 1.1535 0.05641 0.04806 0.0078 0.1360 1.0000
11.750 1.1352 0.05943 0.05146 0.0125 0.1334 1.0000
12.000 1.1439 0.06261 0.05464 0.0141 0.1237 1.0000
12.250 1.1196 0.06575 0.05810 0.0183 0.1228 1.0000
12.500 1.0947 0.06944 0.06208 0.0215 0.1224 1.0000
12.750 1.0677 0.07362 0.06649 0.0238 0.1222 1.0000
13.000 1.0412 0.07839 0.07146 0.0250 0.1227 1.0000
13.250 1.0145 0.08377 0.07699 0.0252 0.1234 1.0000
13.500 0.9891 0.08979 0.08311 0.0245 0.1242 1.0000
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Polar data table (+)
Polar graphs
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