E211 (10.96%) (e211-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 200,000 Max Cl/Cd: 78.87 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e211-il-200000.txt Download as CSV file: xf-e211-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3511 0.09796 0.09463 -0.0373 1.0000 0.0602
-9.750 -0.3695 0.09322 0.08994 -0.0407 1.0000 0.0610
-9.500 -0.3822 0.08856 0.08534 -0.0429 1.0000 0.0612
-9.250 -0.3742 0.08407 0.08087 -0.0397 1.0000 0.0628
-9.000 -0.3674 0.08170 0.07851 -0.0378 1.0000 0.0640
-8.750 -0.3676 0.07870 0.07554 -0.0369 1.0000 0.0653
-8.500 -0.3725 0.07525 0.07213 -0.0366 1.0000 0.0668
-8.250 -0.3816 0.07147 0.06840 -0.0366 1.0000 0.0681
-8.000 -0.3958 0.06742 0.06440 -0.0369 1.0000 0.0695
-7.750 -0.5616 0.06599 0.06252 -0.0500 1.0000 0.0621
-7.500 -0.5384 0.06512 0.06192 -0.0458 1.0000 0.0642
-7.250 -0.5363 0.06301 0.05982 -0.0444 1.0000 0.0660
-7.000 -0.5394 0.05949 0.05623 -0.0446 1.0000 0.0679
-6.750 -0.5502 0.05686 0.05275 -0.0477 1.0000 0.0743
-6.500 -0.5454 0.04968 0.04578 -0.0478 1.0000 0.0763
-6.250 -0.5341 0.04710 0.04321 -0.0470 1.0000 0.0779
-6.000 -0.5113 0.03198 0.02626 -0.0493 1.0000 0.0374
-5.750 -0.4895 0.02792 0.02179 -0.0498 1.0000 0.0356
-5.500 -0.4657 0.02516 0.01859 -0.0497 1.0000 0.0344
-5.250 -0.4289 0.02282 0.01583 -0.0517 0.9973 0.0339
-5.000 -0.3901 0.02119 0.01392 -0.0539 0.9943 0.0344
-4.750 -0.3523 0.02018 0.01274 -0.0560 0.9897 0.0366
-4.500 -0.3124 0.01939 0.01178 -0.0585 0.9858 0.0382
-4.250 -0.2764 0.01778 0.01018 -0.0605 0.9818 0.0407
-4.000 -0.2386 0.01697 0.00937 -0.0628 0.9765 0.0455
-3.750 -0.1967 0.01613 0.00850 -0.0659 0.9729 0.0572
-3.500 -0.1613 0.01464 0.00766 -0.0683 0.9672 0.1770
-3.250 -0.1224 0.01376 0.00736 -0.0714 0.9622 0.3152
-3.000 -0.0845 0.01309 0.00744 -0.0739 0.9579 0.5073
-2.500 -0.0109 0.01293 0.00741 -0.0770 0.9449 0.6224
-2.250 0.0224 0.01283 0.00727 -0.0778 0.9364 0.6512
-2.000 0.0609 0.01270 0.00714 -0.0795 0.9311 0.6762
-1.750 0.0944 0.01253 0.00695 -0.0803 0.9228 0.6958
-1.500 0.1359 0.01229 0.00670 -0.0826 0.9192 0.7141
-1.250 0.1663 0.01209 0.00650 -0.0827 0.9094 0.7297
-1.000 0.2078 0.01177 0.00618 -0.0850 0.9058 0.7453
-0.750 0.2395 0.01154 0.00594 -0.0854 0.8963 0.7593
-0.500 0.2823 0.01122 0.00563 -0.0879 0.8919 0.7734
-0.250 0.3153 0.01099 0.00541 -0.0886 0.8814 0.7866
0.000 0.3533 0.01074 0.00516 -0.0902 0.8727 0.7998
0.250 0.3917 0.01050 0.00491 -0.0920 0.8631 0.8121
0.500 0.4247 0.01033 0.00475 -0.0926 0.8499 0.8237
0.750 0.4573 0.01020 0.00461 -0.0933 0.8359 0.8354
1.000 0.4883 0.01012 0.00451 -0.0936 0.8212 0.8476
1.250 0.5175 0.01008 0.00444 -0.0936 0.8060 0.8605
1.500 0.5447 0.01006 0.00441 -0.0931 0.7906 0.8745
1.750 0.5699 0.01006 0.00438 -0.0922 0.7753 0.8900
2.000 0.5936 0.01005 0.00437 -0.0910 0.7601 0.9084
2.250 0.6187 0.01005 0.00436 -0.0901 0.7448 0.9312
2.500 0.6514 0.01005 0.00436 -0.0909 0.7284 0.9588
2.750 0.6937 0.01010 0.00439 -0.0941 0.7105 1.0000
3.000 0.7220 0.01027 0.00450 -0.0946 0.6939 1.0000
3.250 0.7501 0.01045 0.00462 -0.0949 0.6774 1.0000
3.500 0.7774 0.01064 0.00475 -0.0949 0.6607 1.0000
3.750 0.8040 0.01084 0.00489 -0.0947 0.6437 1.0000
4.000 0.8302 0.01105 0.00505 -0.0944 0.6268 1.0000
4.250 0.8553 0.01124 0.00524 -0.0938 0.6090 1.0000
4.500 0.8800 0.01144 0.00543 -0.0932 0.5904 1.0000
4.750 0.9044 0.01165 0.00563 -0.0925 0.5716 1.0000
5.000 0.9286 0.01189 0.00584 -0.0917 0.5522 1.0000
5.250 0.9516 0.01210 0.00607 -0.0907 0.5297 1.0000
5.500 0.9740 0.01235 0.00629 -0.0895 0.5054 1.0000
5.750 0.9955 0.01263 0.00653 -0.0882 0.4780 1.0000
6.000 1.0162 0.01295 0.00683 -0.0868 0.4465 1.0000
6.250 1.0349 0.01337 0.00713 -0.0851 0.4064 1.0000
6.500 1.0516 0.01393 0.00751 -0.0830 0.3550 1.0000
6.750 1.0648 0.01477 0.00801 -0.0806 0.2901 1.0000
7.000 1.0773 0.01580 0.00869 -0.0782 0.2263 1.0000
7.250 1.0903 0.01688 0.00945 -0.0761 0.1736 1.0000
7.500 1.1053 0.01785 0.01022 -0.0742 0.1349 1.0000
7.750 1.1199 0.01886 0.01107 -0.0723 0.1014 1.0000
8.000 1.1283 0.02040 0.01230 -0.0693 0.0585 1.0000
8.250 1.1334 0.02204 0.01381 -0.0657 0.0383 1.0000
8.500 1.1410 0.02339 0.01518 -0.0625 0.0324 1.0000
8.750 1.1510 0.02455 0.01643 -0.0598 0.0293 1.0000
9.000 1.1566 0.02609 0.01800 -0.0566 0.0274 1.0000
9.250 1.1635 0.02780 0.01978 -0.0537 0.0262 1.0000
9.500 1.1756 0.02921 0.02132 -0.0516 0.0252 1.0000
9.750 1.1887 0.03080 0.02301 -0.0497 0.0243 1.0000
10.000 1.2038 0.03252 0.02484 -0.0481 0.0236 1.0000
10.250 1.2207 0.03439 0.02684 -0.0469 0.0230 1.0000
10.500 1.2383 0.03645 0.02907 -0.0458 0.0225 1.0000
10.750 1.2528 0.03840 0.03116 -0.0444 0.0218 1.0000
11.000 1.2657 0.04047 0.03335 -0.0431 0.0212 1.0000
11.250 1.2812 0.04393 0.03697 -0.0425 0.0203 1.0000
11.500 1.2887 0.04777 0.04112 -0.0410 0.0201 1.0000
11.750 1.2896 0.05094 0.04457 -0.0387 0.0201 1.0000
12.000 1.2866 0.05391 0.04781 -0.0362 0.0201 1.0000
12.250 1.2808 0.05685 0.05101 -0.0339 0.0202 1.0000
12.500 1.2724 0.05990 0.05432 -0.0319 0.0203 1.0000
12.750 1.2614 0.06325 0.05792 -0.0304 0.0204 1.0000
13.000 1.2477 0.06694 0.06187 -0.0294 0.0206 1.0000
13.250 1.2302 0.07133 0.06657 -0.0292 0.0208 1.0000
13.500 1.2043 0.07736 0.07296 -0.0302 0.0213 1.0000
13.750 1.1650 0.08586 0.08187 -0.0335 0.0219 1.0000
14.000 1.1297 0.09516 0.09148 -0.0384 0.0225 1.0000
14.250 1.0973 0.10512 0.10168 -0.0446 0.0229 1.0000
14.500 1.0641 0.11673 0.11349 -0.0525 0.0233 1.0000
14.750 1.0247 0.13222 0.12914 -0.0633 0.0240 1.0000
15.000 0.9890 0.14964 0.14659 -0.0741 0.0254 1.0000
15.250 0.9798 0.15794 0.15486 -0.0782 0.0263 1.0000
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Polar data table (+)
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