E211 (10.96%) (e211-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E211 (10.96%) (e211-il) Reynolds number: 200,000 Max Cl/Cd: 74.71 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e211-il-200000-n5.txt Download as CSV file: xf-e211-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4754 0.09274 0.08908 -0.0389 1.0000 0.0169
-10.000 -0.4817 0.08828 0.08467 -0.0401 1.0000 0.0167
-9.750 -0.4900 0.08344 0.07987 -0.0415 1.0000 0.0165
-9.500 -0.5022 0.07781 0.07430 -0.0435 1.0000 0.0163
-9.250 -0.5214 0.07007 0.06662 -0.0470 1.0000 0.0161
-9.000 -0.5555 0.06065 0.05719 -0.0526 1.0000 0.0158
-8.750 -0.5841 0.05672 0.05323 -0.0530 1.0000 0.0157
-8.500 -0.6056 0.05177 0.04810 -0.0538 1.0000 0.0156
-8.250 -0.6198 0.04690 0.04297 -0.0536 1.0000 0.0154
-8.000 -0.6207 0.04160 0.03727 -0.0549 0.9988 0.0153
-7.750 -0.5997 0.03572 0.03074 -0.0594 0.9948 0.0152
-7.500 -0.5755 0.03157 0.02602 -0.0619 0.9909 0.0152
-7.250 -0.5474 0.02842 0.02234 -0.0640 0.9876 0.0153
-7.000 -0.5162 0.02597 0.01945 -0.0660 0.9851 0.0155
-6.750 -0.4875 0.02410 0.01724 -0.0670 0.9816 0.0158
-6.500 -0.4574 0.02254 0.01541 -0.0681 0.9779 0.0162
-6.250 -0.4250 0.02129 0.01394 -0.0695 0.9750 0.0166
-6.000 -0.3918 0.01996 0.01247 -0.0713 0.9727 0.0177
-5.750 -0.3649 0.01901 0.01148 -0.0716 0.9675 0.0187
-5.500 -0.3334 0.01809 0.01047 -0.0727 0.9635 0.0193
-5.250 -0.2992 0.01724 0.00953 -0.0744 0.9606 0.0200
-5.000 -0.2710 0.01652 0.00870 -0.0747 0.9549 0.0209
-4.750 -0.2390 0.01588 0.00795 -0.0758 0.9502 0.0219
-4.500 -0.2038 0.01522 0.00722 -0.0776 0.9471 0.0239
-4.250 -0.1768 0.01470 0.00666 -0.0776 0.9397 0.0274
-4.000 -0.1429 0.01410 0.00609 -0.0790 0.9354 0.0403
-3.750 -0.1133 0.01346 0.00561 -0.0797 0.9290 0.0774
-3.500 -0.0814 0.01287 0.00522 -0.0809 0.9232 0.1272
-3.250 -0.0488 0.01227 0.00486 -0.0822 0.9179 0.1918
-3.000 -0.0194 0.01155 0.00455 -0.0831 0.9104 0.2944
-2.750 0.0149 0.01074 0.00436 -0.0848 0.9061 0.4470
-2.500 0.0436 0.01051 0.00428 -0.0849 0.8964 0.5161
-2.250 0.0789 0.01033 0.00411 -0.0862 0.8898 0.5584
-2.000 0.1128 0.01019 0.00397 -0.0873 0.8810 0.5846
-1.750 0.1489 0.01007 0.00381 -0.0888 0.8725 0.6068
-1.500 0.1874 0.00993 0.00365 -0.0908 0.8638 0.6260
-1.250 0.2229 0.00983 0.00352 -0.0922 0.8523 0.6424
-1.000 0.2595 0.00974 0.00339 -0.0938 0.8399 0.6574
-0.750 0.2952 0.00968 0.00328 -0.0952 0.8264 0.6713
-0.500 0.3293 0.00965 0.00320 -0.0963 0.8115 0.6844
-0.250 0.3617 0.00964 0.00314 -0.0971 0.7958 0.6968
0.000 0.3924 0.00967 0.00310 -0.0975 0.7797 0.7085
0.250 0.4216 0.00970 0.00310 -0.0976 0.7636 0.7188
0.500 0.4500 0.00976 0.00310 -0.0976 0.7478 0.7290
0.750 0.4779 0.00983 0.00312 -0.0975 0.7322 0.7392
1.000 0.5048 0.00990 0.00316 -0.0971 0.7172 0.7482
1.250 0.5315 0.00998 0.00322 -0.0968 0.7026 0.7579
1.500 0.5579 0.01008 0.00329 -0.0964 0.6883 0.7685
1.750 0.5837 0.01016 0.00337 -0.0958 0.6743 0.7790
2.000 0.6092 0.01025 0.00348 -0.0953 0.6604 0.7903
2.250 0.6344 0.01035 0.00358 -0.0946 0.6460 0.8029
2.500 0.6590 0.01045 0.00369 -0.0938 0.6311 0.8169
2.750 0.6829 0.01056 0.00380 -0.0928 0.6157 0.8322
3.000 0.7063 0.01066 0.00393 -0.0917 0.6002 0.8498
3.250 0.7293 0.01076 0.00405 -0.0905 0.5849 0.8713
3.500 0.7516 0.01084 0.00416 -0.0892 0.5691 0.8985
3.750 0.7771 0.01092 0.00427 -0.0886 0.5514 0.9392
4.000 0.8071 0.01106 0.00443 -0.0891 0.5317 1.0000
4.250 0.8322 0.01130 0.00461 -0.0887 0.5122 1.0000
4.500 0.8569 0.01155 0.00482 -0.0881 0.4915 1.0000
4.750 0.8811 0.01181 0.00504 -0.0875 0.4689 1.0000
5.000 0.9047 0.01211 0.00531 -0.0867 0.4445 1.0000
5.250 0.9274 0.01245 0.00558 -0.0858 0.4168 1.0000
5.500 0.9491 0.01285 0.00588 -0.0848 0.3832 1.0000
5.750 0.9691 0.01336 0.00623 -0.0834 0.3421 1.0000
6.000 0.9872 0.01402 0.00668 -0.0819 0.2916 1.0000
6.250 1.0037 0.01485 0.00721 -0.0802 0.2355 1.0000
6.500 1.0203 0.01573 0.00782 -0.0785 0.1854 1.0000
6.750 1.0376 0.01658 0.00845 -0.0770 0.1453 1.0000
7.000 1.0548 0.01744 0.00911 -0.0756 0.1098 1.0000
7.250 1.0726 0.01824 0.00980 -0.0741 0.0838 1.0000
7.500 1.0901 0.01904 0.01050 -0.0727 0.0622 1.0000
7.750 1.1067 0.01989 0.01127 -0.0710 0.0440 1.0000
8.000 1.1217 0.02085 0.01216 -0.0692 0.0284 1.0000
8.250 1.1353 0.02183 0.01311 -0.0670 0.0200 1.0000
8.500 1.1493 0.02272 0.01404 -0.0649 0.0165 1.0000
8.750 1.1628 0.02364 0.01506 -0.0628 0.0147 1.0000
9.000 1.1761 0.02456 0.01609 -0.0606 0.0137 1.0000
9.250 1.1883 0.02556 0.01720 -0.0585 0.0130 1.0000
9.500 1.1990 0.02664 0.01839 -0.0562 0.0124 1.0000
9.750 1.2069 0.02793 0.01978 -0.0536 0.0119 1.0000
10.000 1.2131 0.02935 0.02131 -0.0510 0.0116 1.0000
10.250 1.2204 0.03073 0.02283 -0.0487 0.0113 1.0000
10.500 1.2269 0.03223 0.02448 -0.0465 0.0111 1.0000
10.750 1.2324 0.03387 0.02626 -0.0443 0.0109 1.0000
11.000 1.2376 0.03562 0.02814 -0.0423 0.0107 1.0000
11.250 1.2424 0.03751 0.03017 -0.0405 0.0105 1.0000
11.500 1.2473 0.03943 0.03224 -0.0389 0.0102 1.0000
11.750 1.2516 0.04151 0.03447 -0.0375 0.0099 1.0000
12.000 1.2555 0.04362 0.03671 -0.0363 0.0095 1.0000
12.250 1.2583 0.04599 0.03922 -0.0353 0.0093 1.0000
12.500 1.2601 0.04848 0.04185 -0.0344 0.0091 1.0000
12.750 1.2607 0.05122 0.04473 -0.0338 0.0089 1.0000
13.250 1.2584 0.05753 0.05136 -0.0332 0.0086 1.0000
13.500 1.2552 0.06114 0.05514 -0.0333 0.0085 1.0000
13.750 1.2508 0.06502 0.05921 -0.0337 0.0084 1.0000
14.000 1.2440 0.06938 0.06375 -0.0344 0.0083 1.0000
14.250 1.2358 0.07412 0.06870 -0.0355 0.0083 1.0000
14.500 1.2269 0.07911 0.07389 -0.0371 0.0083 1.0000
14.750 1.2157 0.08469 0.07967 -0.0392 0.0082 1.0000
15.250 1.1915 0.09697 0.09237 -0.0451 0.0082 1.0000
15.500 1.1780 0.10382 0.09942 -0.0488 0.0082 1.0000
16.000 1.1498 0.11897 0.11497 -0.0578 0.0083 1.0000
16.250 1.1350 0.12739 0.12357 -0.0632 0.0083 1.0000
16.500 1.1191 0.13660 0.13298 -0.0693 0.0084 1.0000
16.750 1.0983 0.14799 0.14459 -0.0768 0.0085 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E211 (10.96%) (e211-il)