E211 (10.96%) (e211-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 100,000 Max Cl/Cd: 57.56 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e211-il-100000-n5.txt Download as CSV file: xf-e211-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4586 0.09026 0.08519 -0.0406 1.0000 0.0267
-9.250 -0.4672 0.08534 0.08035 -0.0422 1.0000 0.0263
-9.000 -0.4799 0.07973 0.07482 -0.0443 1.0000 0.0259
-8.750 -0.4987 0.07268 0.06784 -0.0476 1.0000 0.0253
-8.500 -0.5318 0.06563 0.06084 -0.0508 1.0000 0.0247
-8.250 -0.5594 0.05945 0.05455 -0.0532 1.0000 0.0243
-8.000 -0.5800 0.05342 0.04823 -0.0541 1.0000 0.0238
-7.750 -0.5900 0.04791 0.04228 -0.0544 1.0000 0.0235
-7.500 -0.5878 0.04380 0.03777 -0.0541 1.0000 0.0234
-7.250 -0.5795 0.04037 0.03397 -0.0537 1.0000 0.0235
-7.000 -0.5665 0.03804 0.03139 -0.0533 1.0000 0.0241
-6.750 -0.5512 0.03597 0.02908 -0.0528 1.0000 0.0251
-6.500 -0.5342 0.03368 0.02643 -0.0524 1.0000 0.0261
-6.250 -0.5152 0.03130 0.02364 -0.0520 1.0000 0.0267
-6.000 -0.4945 0.02910 0.02106 -0.0516 1.0000 0.0271
-5.750 -0.4682 0.02718 0.01876 -0.0519 0.9988 0.0276
-5.500 -0.4337 0.02545 0.01671 -0.0537 0.9953 0.0283
-5.250 -0.3997 0.02405 0.01508 -0.0552 0.9913 0.0292
-5.000 -0.3658 0.02271 0.01367 -0.0570 0.9871 0.0306
-4.750 -0.3310 0.02180 0.01268 -0.0590 0.9828 0.0330
-4.500 -0.2970 0.02105 0.01179 -0.0606 0.9772 0.0377
-4.250 -0.2604 0.02009 0.01079 -0.0629 0.9730 0.0436
-4.000 -0.2282 0.01920 0.00988 -0.0641 0.9665 0.0553
-3.750 -0.1925 0.01830 0.00914 -0.0663 0.9614 0.0987
-3.500 -0.1606 0.01734 0.00871 -0.0680 0.9549 0.1939
-3.250 -0.1271 0.01632 0.00836 -0.0702 0.9490 0.3367
-3.000 -0.0971 0.01577 0.00833 -0.0708 0.9416 0.4641
-2.750 -0.0630 0.01563 0.00825 -0.0718 0.9349 0.5445
-2.500 -0.0334 0.01555 0.00815 -0.0719 0.9257 0.5892
-2.250 0.0021 0.01545 0.00801 -0.0731 0.9198 0.6237
-2.000 0.0308 0.01536 0.00786 -0.0730 0.9098 0.6510
-1.750 0.0621 0.01525 0.00772 -0.0733 0.9016 0.6741
-1.500 0.0954 0.01510 0.00752 -0.0740 0.8940 0.6958
-1.250 0.1249 0.01497 0.00735 -0.0739 0.8845 0.7142
-1.000 0.1603 0.01478 0.00712 -0.0750 0.8780 0.7322
-0.750 0.1896 0.01465 0.00697 -0.0749 0.8672 0.7486
-0.500 0.2223 0.01450 0.00679 -0.0755 0.8581 0.7643
-0.250 0.2576 0.01433 0.00659 -0.0766 0.8496 0.7789
0.000 0.2886 0.01421 0.00644 -0.0770 0.8383 0.7925
0.250 0.3215 0.01407 0.00628 -0.0777 0.8276 0.8056
0.500 0.3564 0.01391 0.00610 -0.0788 0.8175 0.8185
0.750 0.3891 0.01380 0.00597 -0.0794 0.8057 0.8316
1.000 0.4199 0.01371 0.00588 -0.0797 0.7928 0.8457
1.250 0.4504 0.01363 0.00580 -0.0800 0.7798 0.8606
1.500 0.4806 0.01356 0.00575 -0.0801 0.7666 0.8776
1.750 0.5114 0.01351 0.00571 -0.0805 0.7534 0.8976
2.000 0.5447 0.01347 0.00568 -0.0813 0.7400 0.9217
2.250 0.5832 0.01347 0.00570 -0.0834 0.7261 0.9539
2.500 0.6205 0.01352 0.00573 -0.0855 0.7117 1.0000
2.750 0.6510 0.01367 0.00584 -0.0862 0.6975 1.0000
3.000 0.6805 0.01385 0.00598 -0.0867 0.6827 1.0000
3.250 0.7089 0.01404 0.00616 -0.0869 0.6672 1.0000
3.500 0.7365 0.01424 0.00634 -0.0868 0.6510 1.0000
3.750 0.7635 0.01446 0.00654 -0.0867 0.6342 1.0000
4.000 0.7900 0.01468 0.00678 -0.0864 0.6171 1.0000
4.250 0.8161 0.01492 0.00700 -0.0860 0.5996 1.0000
4.500 0.8414 0.01516 0.00725 -0.0854 0.5808 1.0000
4.750 0.8656 0.01542 0.00753 -0.0847 0.5605 1.0000
5.000 0.8897 0.01569 0.00782 -0.0839 0.5397 1.0000
5.250 0.9128 0.01597 0.00814 -0.0829 0.5171 1.0000
5.500 0.9355 0.01629 0.00844 -0.0819 0.4929 1.0000
5.750 0.9572 0.01663 0.00879 -0.0807 0.4657 1.0000
6.000 0.9780 0.01702 0.00918 -0.0793 0.4354 1.0000
6.250 0.9978 0.01747 0.00960 -0.0778 0.4002 1.0000
6.500 1.0158 0.01804 0.01007 -0.0761 0.3593 1.0000
6.750 1.0323 0.01874 0.01061 -0.0742 0.3131 1.0000
7.000 1.0473 0.01960 0.01128 -0.0722 0.2657 1.0000
7.250 1.0611 0.02061 0.01210 -0.0701 0.2207 1.0000
7.500 1.0741 0.02172 0.01299 -0.0681 0.1783 1.0000
7.750 1.0863 0.02292 0.01395 -0.0660 0.1382 1.0000
8.000 1.0981 0.02416 0.01496 -0.0639 0.1023 1.0000
8.250 1.1104 0.02535 0.01601 -0.0619 0.0758 1.0000
8.500 1.1204 0.02662 0.01718 -0.0595 0.0556 1.0000
8.750 1.1292 0.02799 0.01851 -0.0569 0.0408 1.0000
9.000 1.1360 0.02951 0.02008 -0.0541 0.0335 1.0000
9.250 1.1433 0.03099 0.02166 -0.0514 0.0293 1.0000
9.500 1.1473 0.03270 0.02343 -0.0486 0.0270 1.0000
9.750 1.1536 0.03430 0.02522 -0.0461 0.0252 1.0000
10.000 1.1597 0.03597 0.02705 -0.0438 0.0237 1.0000
10.250 1.1655 0.03770 0.02889 -0.0417 0.0223 1.0000
10.500 1.1697 0.03959 0.03086 -0.0398 0.0211 1.0000
10.750 1.1741 0.04165 0.03306 -0.0380 0.0200 1.0000
11.000 1.1804 0.04369 0.03530 -0.0364 0.0192 1.0000
11.250 1.1860 0.04591 0.03773 -0.0350 0.0184 1.0000
11.500 1.1912 0.04828 0.04028 -0.0337 0.0179 1.0000
11.750 1.1958 0.05080 0.04299 -0.0326 0.0175 1.0000
12.000 1.1993 0.05350 0.04588 -0.0316 0.0171 1.0000
12.250 1.2013 0.05639 0.04896 -0.0308 0.0168 1.0000
12.500 1.2016 0.05951 0.05229 -0.0302 0.0166 1.0000
12.750 1.2000 0.06291 0.05589 -0.0298 0.0164 1.0000
13.000 1.1964 0.06664 0.05983 -0.0298 0.0162 1.0000
13.250 1.1906 0.07072 0.06414 -0.0302 0.0161 1.0000
13.500 1.1826 0.07523 0.06887 -0.0310 0.0160 1.0000
13.750 1.1724 0.08019 0.07407 -0.0323 0.0160 1.0000
14.000 1.1597 0.08571 0.07983 -0.0343 0.0159 1.0000
14.250 1.1448 0.09188 0.08625 -0.0371 0.0160 1.0000
14.500 1.1274 0.09887 0.09350 -0.0407 0.0160 1.0000
14.750 1.1068 0.10705 0.10193 -0.0455 0.0161 1.0000
15.000 1.0819 0.11704 0.11219 -0.0519 0.0163 1.0000
15.250 1.0470 0.13096 0.12639 -0.0613 0.0168 1.0000
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Polar data table (+)
Polar graphs
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