EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 50,000 Max Cl/Cd: 28.31 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2012-il-50000-n5.txt Download as CSV file: xf-eh2012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5377 0.09703 0.09025 -0.0151 1.0000 0.0519
-10.000 -0.5455 0.09057 0.08385 -0.0194 1.0000 0.0519
-9.750 -0.5556 0.08386 0.07717 -0.0241 1.0000 0.0517
-9.500 -0.5705 0.07792 0.07124 -0.0278 1.0000 0.0514
-9.250 -0.5881 0.07291 0.06621 -0.0295 1.0000 0.0511
-9.000 -0.6068 0.06857 0.06180 -0.0294 1.0000 0.0511
-8.750 -0.6213 0.06412 0.05718 -0.0290 1.0000 0.0512
-8.500 -0.6323 0.05974 0.05255 -0.0280 1.0000 0.0516
-8.250 -0.6392 0.05544 0.04791 -0.0266 1.0000 0.0521
-8.000 -0.6416 0.05132 0.04336 -0.0248 1.0000 0.0526
-7.750 -0.6375 0.04769 0.03942 -0.0231 1.0000 0.0535
-7.500 -0.6265 0.04517 0.03675 -0.0217 1.0000 0.0551
-7.250 -0.6136 0.04315 0.03458 -0.0203 1.0000 0.0582
-7.000 -0.6023 0.04049 0.03151 -0.0185 1.0000 0.0617
-6.750 -0.5897 0.03747 0.02785 -0.0165 1.0000 0.0648
-6.500 -0.5727 0.03558 0.02593 -0.0152 1.0000 0.0683
-6.250 -0.5557 0.03398 0.02413 -0.0137 1.0000 0.0740
-6.000 -0.5373 0.03201 0.02185 -0.0122 1.0000 0.0795
-5.750 -0.5197 0.03075 0.02056 -0.0107 1.0000 0.0861
-5.500 -0.5013 0.02936 0.01901 -0.0092 1.0000 0.0940
-5.250 -0.4837 0.02827 0.01785 -0.0076 1.0000 0.1024
-5.000 -0.4678 0.02733 0.01690 -0.0059 1.0000 0.1118
-4.750 -0.4519 0.02647 0.01595 -0.0040 1.0000 0.1217
-4.500 -0.4070 0.02533 0.01481 -0.0077 0.9832 0.1415
-4.250 -0.3625 0.02427 0.01371 -0.0112 0.9659 0.1664
-4.000 -0.3195 0.02319 0.01269 -0.0144 0.9483 0.1975
-3.750 -0.2803 0.02207 0.01178 -0.0171 0.9299 0.2431
-3.500 -0.2472 0.02074 0.01096 -0.0187 0.9112 0.3266
-3.250 -0.2253 0.01923 0.01086 -0.0168 0.8917 0.5577
-3.000 -0.1748 0.01958 0.01159 -0.0171 0.8769 0.7678
-2.750 -0.1341 0.02009 0.01183 -0.0172 0.8583 0.8333
-2.500 -0.0840 0.02061 0.01199 -0.0191 0.8405 0.8762
-2.250 -0.0268 0.02097 0.01197 -0.0228 0.8225 0.9112
-2.000 0.0555 0.02116 0.01174 -0.0314 0.8035 0.9545
-1.750 0.1198 0.02083 0.01105 -0.0381 0.7826 0.9806
-1.500 0.1598 0.02053 0.01048 -0.0408 0.7633 0.9917
-1.250 0.1946 0.02031 0.01002 -0.0426 0.7448 1.0000
-1.000 0.2140 0.02029 0.00983 -0.0415 0.7277 1.0000
-0.750 0.2336 0.02030 0.00968 -0.0403 0.7117 1.0000
-0.500 0.2535 0.02032 0.00956 -0.0392 0.6968 1.0000
-0.250 0.2736 0.02037 0.00946 -0.0381 0.6826 1.0000
0.000 0.2939 0.02042 0.00939 -0.0370 0.6692 1.0000
0.250 0.3144 0.02049 0.00933 -0.0359 0.6565 1.0000
0.500 0.3349 0.02059 0.00935 -0.0349 0.6434 1.0000
0.750 0.3555 0.02072 0.00941 -0.0339 0.6308 1.0000
1.000 0.3761 0.02086 0.00949 -0.0328 0.6188 1.0000
1.250 0.3966 0.02102 0.00957 -0.0317 0.6076 1.0000
1.500 0.4172 0.02118 0.00964 -0.0305 0.5972 1.0000
1.750 0.4381 0.02141 0.00986 -0.0296 0.5855 1.0000
2.000 0.4589 0.02165 0.01008 -0.0286 0.5746 1.0000
2.250 0.4796 0.02187 0.01024 -0.0274 0.5647 1.0000
2.500 0.5002 0.02214 0.01049 -0.0263 0.5544 1.0000
2.750 0.5204 0.02245 0.01084 -0.0252 0.5439 1.0000
3.000 0.5410 0.02273 0.01108 -0.0240 0.5347 1.0000
3.250 0.5612 0.02305 0.01141 -0.0228 0.5249 1.0000
3.500 0.5810 0.02344 0.01183 -0.0216 0.5149 1.0000
3.750 0.6018 0.02372 0.01210 -0.0204 0.5065 1.0000
4.000 0.6213 0.02416 0.01261 -0.0192 0.4964 1.0000
4.250 0.6410 0.02459 0.01307 -0.0179 0.4871 1.0000
4.750 0.6805 0.02547 0.01408 -0.0154 0.4690 1.0000
5.000 0.7010 0.02586 0.01449 -0.0142 0.4608 1.0000
5.250 0.7203 0.02638 0.01510 -0.0129 0.4515 1.0000
5.500 0.7392 0.02694 0.01577 -0.0117 0.4424 1.0000
5.750 0.7604 0.02731 0.01616 -0.0104 0.4345 1.0000
6.000 0.7776 0.02803 0.01704 -0.0091 0.4248 1.0000
6.250 0.7983 0.02847 0.01752 -0.0078 0.4168 1.0000
6.500 0.8162 0.02914 0.01833 -0.0065 0.4075 1.0000
6.750 0.8342 0.02982 0.01916 -0.0052 0.3986 1.0000
7.000 0.8555 0.03022 0.01962 -0.0040 0.3906 1.0000
7.250 0.8708 0.03115 0.02074 -0.0026 0.3808 1.0000
7.500 0.8915 0.03162 0.02129 -0.0014 0.3727 1.0000
7.750 0.9081 0.03243 0.02231 0.0000 0.3634 1.0000
8.000 0.9241 0.03328 0.02334 0.0013 0.3540 1.0000
8.250 0.9470 0.03357 0.02368 0.0024 0.3460 1.0000
8.500 0.9582 0.03476 0.02512 0.0040 0.3356 1.0000
8.750 0.9745 0.03556 0.02608 0.0054 0.3264 1.0000
9.000 0.9953 0.03594 0.02659 0.0066 0.3174 1.0000
9.250 1.0037 0.03727 0.02817 0.0083 0.3070 1.0000
9.500 1.0180 0.03812 0.02918 0.0098 0.2974 1.0000
9.750 1.0399 0.03826 0.02940 0.0111 0.2877 1.0000
10.000 1.0424 0.03985 0.03125 0.0131 0.2769 1.0000
10.250 1.0488 0.04103 0.03261 0.0150 0.2664 1.0000
10.500 1.0597 0.04173 0.03344 0.0168 0.2556 1.0000
10.750 1.0695 0.04226 0.03408 0.0187 0.2437 1.0000
11.000 1.0625 0.04390 0.03588 0.0213 0.2331 1.0000
11.250 1.0515 0.04608 0.03817 0.0233 0.2229 1.0000
11.500 1.0451 0.04803 0.04018 0.0245 0.2112 1.0000
11.750 1.0379 0.05030 0.04250 0.0250 0.1989 1.0000
12.000 1.0298 0.05303 0.04526 0.0249 0.1863 1.0000
12.250 1.0204 0.05623 0.04848 0.0243 0.1736 1.0000
12.500 1.0114 0.05969 0.05195 0.0234 0.1610 1.0000
12.750 0.9981 0.06417 0.05651 0.0218 0.1493 1.0000
13.000 0.9856 0.06878 0.06118 0.0201 0.1379 1.0000
13.250 0.9749 0.07323 0.06565 0.0185 0.1265 1.0000
13.500 0.9654 0.07759 0.06998 0.0170 0.1152 1.0000
13.750 0.9569 0.08186 0.07419 0.0155 0.1044 1.0000
14.000 0.9502 0.08591 0.07811 0.0141 0.0945 1.0000
14.250 0.9404 0.09099 0.08323 0.0121 0.0864 1.0000
14.500 0.9328 0.09576 0.08798 0.0104 0.0794 1.0000
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Polar data table (+)
Polar graphs
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