E207 (12.04%) (e207-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E207 (12.04%) (e207-il) Reynolds number: 200,000 Max Cl/Cd: 73.82 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e207-il-200000.txt Download as CSV file: xf-e207-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E207 (12.04%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3334 0.09134 0.08808 -0.0340 1.0000 0.0663
-9.750 -0.3629 0.08454 0.08136 -0.0412 1.0000 0.0687
-9.500 -0.3851 0.07761 0.07448 -0.0469 1.0000 0.0690
-9.250 -0.3804 0.07262 0.06953 -0.0447 1.0000 0.0703
-9.000 -0.3671 0.07059 0.06751 -0.0421 1.0000 0.0716
-8.750 -0.3649 0.06738 0.06432 -0.0418 1.0000 0.0730
-8.500 -0.3712 0.06315 0.06013 -0.0428 1.0000 0.0744
-8.250 -0.3881 0.05787 0.05492 -0.0453 1.0000 0.0753
-8.000 -0.5267 0.05982 0.05648 -0.0496 1.0000 0.0713
-7.750 -0.5224 0.05750 0.05420 -0.0479 1.0000 0.0725
-7.500 -0.5245 0.05495 0.05163 -0.0459 1.0000 0.0740
-7.250 -0.5302 0.05232 0.04892 -0.0436 1.0000 0.0759
-7.000 -0.5763 0.03724 0.03251 -0.0382 0.9990 0.0419
-6.750 -0.5501 0.02895 0.02293 -0.0403 0.9911 0.0362
-6.500 -0.5121 0.02656 0.02033 -0.0434 0.9847 0.0379
-6.250 -0.4747 0.02432 0.01778 -0.0458 0.9768 0.0391
-6.000 -0.4339 0.02199 0.01510 -0.0484 0.9711 0.0396
-5.750 -0.3966 0.02028 0.01315 -0.0502 0.9616 0.0408
-5.500 -0.3533 0.01889 0.01159 -0.0532 0.9560 0.0433
-5.250 -0.3170 0.01751 0.01010 -0.0547 0.9449 0.0459
-5.000 -0.2825 0.01615 0.00877 -0.0561 0.9326 0.0494
-4.750 -0.2475 0.01522 0.00776 -0.0573 0.9189 0.0547
-4.500 -0.2153 0.01418 0.00672 -0.0581 0.9034 0.0660
-4.250 -0.1874 0.01290 0.00572 -0.0582 0.8864 0.1225
-4.000 -0.1608 0.01210 0.00519 -0.0580 0.8685 0.1987
-3.750 -0.1372 0.01151 0.00485 -0.0573 0.8490 0.2797
-3.500 -0.1150 0.01098 0.00468 -0.0562 0.8311 0.3860
-3.250 -0.0922 0.01071 0.00460 -0.0550 0.8146 0.4746
-3.000 -0.0684 0.01056 0.00450 -0.0539 0.7993 0.5310
-2.750 -0.0440 0.01046 0.00442 -0.0529 0.7851 0.5749
-2.500 -0.0194 0.01039 0.00434 -0.0520 0.7718 0.6134
-2.250 0.0051 0.01031 0.00428 -0.0509 0.7596 0.6517
-2.000 0.0297 0.01024 0.00422 -0.0499 0.7486 0.6900
-1.750 0.0542 0.01017 0.00418 -0.0488 0.7375 0.7270
-1.500 0.0788 0.01010 0.00417 -0.0477 0.7268 0.7655
-1.250 0.1037 0.01007 0.00416 -0.0466 0.7174 0.8070
-1.000 0.1308 0.01006 0.00418 -0.0458 0.7080 0.8501
-0.750 0.1644 0.01014 0.00426 -0.0463 0.6985 0.8904
-0.500 0.2050 0.01029 0.00430 -0.0484 0.6903 0.9231
-0.250 0.2497 0.01044 0.00436 -0.0515 0.6806 0.9480
0.000 0.2979 0.01060 0.00439 -0.0556 0.6720 0.9667
0.250 0.3484 0.01070 0.00436 -0.0602 0.6635 0.9819
0.500 0.4008 0.01073 0.00430 -0.0655 0.6544 0.9943
0.750 0.4378 0.01075 0.00420 -0.0678 0.6472 1.0000
1.000 0.4580 0.01081 0.00422 -0.0667 0.6390 1.0000
1.250 0.4800 0.01092 0.00422 -0.0658 0.6325 1.0000
1.500 0.5018 0.01102 0.00433 -0.0648 0.6247 1.0000
1.750 0.5250 0.01116 0.00437 -0.0640 0.6183 1.0000
2.000 0.5477 0.01130 0.00451 -0.0631 0.6109 1.0000
2.250 0.5715 0.01145 0.00461 -0.0624 0.6045 1.0000
2.500 0.5947 0.01161 0.00478 -0.0616 0.5974 1.0000
2.750 0.6187 0.01177 0.00490 -0.0609 0.5907 1.0000
3.000 0.6425 0.01196 0.00508 -0.0601 0.5841 1.0000
3.250 0.6665 0.01212 0.00524 -0.0594 0.5769 1.0000
3.500 0.6907 0.01231 0.00542 -0.0587 0.5702 1.0000
3.750 0.7145 0.01247 0.00559 -0.0579 0.5625 1.0000
4.000 0.7388 0.01265 0.00576 -0.0572 0.5553 1.0000
4.250 0.7627 0.01279 0.00594 -0.0564 0.5471 1.0000
4.500 0.7866 0.01296 0.00613 -0.0556 0.5393 1.0000
4.750 0.8108 0.01309 0.00625 -0.0548 0.5309 1.0000
5.000 0.8341 0.01323 0.00646 -0.0539 0.5218 1.0000
5.250 0.8590 0.01337 0.00657 -0.0532 0.5136 1.0000
5.500 0.8819 0.01348 0.00678 -0.0523 0.5036 1.0000
5.750 0.9055 0.01361 0.00696 -0.0514 0.4939 1.0000
6.000 0.9298 0.01373 0.00707 -0.0506 0.4843 1.0000
6.250 0.9525 0.01382 0.00725 -0.0496 0.4727 1.0000
6.500 0.9752 0.01392 0.00742 -0.0486 0.4603 1.0000
6.750 0.9978 0.01403 0.00760 -0.0475 0.4472 1.0000
7.000 1.0200 0.01414 0.00779 -0.0464 0.4328 1.0000
7.250 1.0417 0.01428 0.00797 -0.0452 0.4165 1.0000
7.500 1.0627 0.01446 0.00816 -0.0439 0.3984 1.0000
7.750 1.0830 0.01467 0.00845 -0.0426 0.3760 1.0000
8.000 1.1019 0.01497 0.00876 -0.0410 0.3497 1.0000
8.250 1.1186 0.01542 0.00917 -0.0392 0.3161 1.0000
8.500 1.1321 0.01610 0.00971 -0.0370 0.2745 1.0000
8.750 1.1409 0.01711 0.01046 -0.0342 0.2282 1.0000
9.000 1.1468 0.01832 0.01141 -0.0312 0.1855 1.0000
9.250 1.1526 0.01952 0.01242 -0.0283 0.1501 1.0000
9.500 1.1572 0.02071 0.01345 -0.0252 0.1229 1.0000
9.750 1.1589 0.02188 0.01451 -0.0216 0.1047 1.0000
10.000 1.1610 0.02309 0.01569 -0.0184 0.0896 1.0000
10.250 1.1638 0.02437 0.01695 -0.0156 0.0755 1.0000
10.500 1.1638 0.02592 0.01846 -0.0128 0.0645 1.0000
10.750 1.1610 0.02781 0.02032 -0.0103 0.0540 1.0000
11.000 1.1577 0.02994 0.02247 -0.0081 0.0450 1.0000
11.250 1.1558 0.03219 0.02480 -0.0064 0.0384 1.0000
11.500 1.1473 0.03514 0.02774 -0.0049 0.0347 1.0000
11.750 1.1491 0.03739 0.03011 -0.0038 0.0313 1.0000
12.000 1.1512 0.03963 0.03241 -0.0032 0.0288 1.0000
12.250 1.1450 0.04276 0.03552 -0.0021 0.0265 1.0000
12.500 1.1499 0.04491 0.03781 -0.0015 0.0250 1.0000
12.750 1.1541 0.04718 0.04019 -0.0009 0.0238 1.0000
13.000 1.1576 0.04955 0.04266 -0.0004 0.0224 1.0000
13.250 1.1628 0.05179 0.04499 0.0002 0.0219 1.0000
13.500 1.1670 0.05420 0.04744 0.0008 0.0210 1.0000
13.750 1.1746 0.05667 0.04995 0.0021 0.0201 1.0000
14.000 1.1814 0.05946 0.05290 0.0030 0.0197 1.0000
14.250 1.1833 0.06246 0.05611 0.0031 0.0195 1.0000
14.500 1.1824 0.06586 0.05972 0.0030 0.0193 1.0000
14.750 1.1791 0.06969 0.06379 0.0026 0.0192 1.0000
15.000 1.1726 0.07390 0.06822 0.0017 0.0191 1.0000
15.250 1.1636 0.07860 0.07315 0.0005 0.0191 1.0000
15.500 1.1529 0.08364 0.07840 -0.0012 0.0191 1.0000
15.750 1.1396 0.08927 0.08425 -0.0034 0.0191 1.0000
16.000 1.1237 0.09553 0.09074 -0.0063 0.0190 1.0000
16.250 1.1079 0.10210 0.09751 -0.0094 0.0192 1.0000
16.500 1.0909 0.10916 0.10476 -0.0133 0.0192 1.0000
16.750 1.0722 0.11692 0.11270 -0.0176 0.0194 1.0000
17.000 1.0533 0.12517 0.12111 -0.0224 0.0196 1.0000
17.250 1.0314 0.13455 0.13066 -0.0283 0.0197 1.0000
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Polar data table (+)
Polar graphs
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