E222 (10.17%) (e222-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E222 (10.17%) (e222-il) Reynolds number: 200,000 Max Cl/Cd: 76.61 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e222-il-200000.txt Download as CSV file: xf-e222-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4324 0.11507 0.11132 -0.0307 1.0000 0.0521
-10.500 -0.4438 0.11105 0.10738 -0.0358 1.0000 0.0533
-10.250 -0.4477 0.10711 0.10348 -0.0385 1.0000 0.0535
-10.000 -0.4482 0.10146 0.09788 -0.0379 1.0000 0.0544
-9.750 -0.4361 0.09924 0.09563 -0.0354 1.0000 0.0557
-9.500 -0.4295 0.09680 0.09321 -0.0346 1.0000 0.0573
-9.250 -0.4269 0.09402 0.09045 -0.0346 1.0000 0.0594
-9.000 -0.4302 0.09054 0.08702 -0.0358 1.0000 0.0622
-8.750 -0.3690 0.07490 0.07172 -0.0400 1.0000 0.0682
-8.500 -0.3658 0.07232 0.06917 -0.0385 1.0000 0.0696
-8.250 -0.4911 0.07620 0.07298 -0.0468 1.0000 0.0655
-8.000 -0.5178 0.07134 0.06801 -0.0499 1.0000 0.0658
-7.750 -0.5354 0.06812 0.06461 -0.0502 1.0000 0.0660
-7.500 -0.5302 0.06252 0.05925 -0.0482 1.0000 0.0678
-7.250 -0.5169 0.06242 0.05926 -0.0441 1.0000 0.0700
-7.000 -0.5187 0.05967 0.05648 -0.0434 1.0000 0.0720
-6.750 -0.5235 0.05553 0.05219 -0.0444 1.0000 0.0757
-6.500 -0.5316 0.04958 0.04581 -0.0466 1.0000 0.0812
-6.250 -0.5212 0.04724 0.04352 -0.0453 1.0000 0.0828
-6.000 -0.5057 0.03066 0.02513 -0.0481 1.0000 0.0396
-5.750 -0.4848 0.02667 0.02058 -0.0480 1.0000 0.0368
-5.500 -0.4603 0.02366 0.01696 -0.0477 1.0000 0.0350
-5.250 -0.4281 0.02170 0.01466 -0.0487 0.9982 0.0348
-5.000 -0.3904 0.02022 0.01297 -0.0509 0.9951 0.0356
-4.750 -0.3534 0.01925 0.01188 -0.0529 0.9911 0.0378
-4.500 -0.3159 0.01819 0.01070 -0.0549 0.9871 0.0396
-4.250 -0.2761 0.01729 0.00969 -0.0574 0.9839 0.0412
-4.000 -0.2419 0.01617 0.00856 -0.0589 0.9785 0.0443
-3.750 -0.2027 0.01548 0.00781 -0.0614 0.9740 0.0518
-3.500 -0.1621 0.01393 0.00694 -0.0648 0.9712 0.1747
-3.250 -0.1294 0.01335 0.00670 -0.0663 0.9642 0.2680
-3.000 -0.0897 0.01291 0.00657 -0.0691 0.9597 0.3595
-2.750 -0.0550 0.01254 0.00649 -0.0707 0.9535 0.4456
-2.500 -0.0184 0.01221 0.00643 -0.0725 0.9476 0.5277
-2.250 0.0229 0.01193 0.00631 -0.0750 0.9441 0.5928
-2.000 0.0528 0.01171 0.00622 -0.0752 0.9353 0.6401
-1.750 0.0931 0.01146 0.00607 -0.0773 0.9314 0.6884
-1.500 0.1245 0.01127 0.00597 -0.0775 0.9236 0.7300
-1.250 0.1626 0.01102 0.00579 -0.0790 0.9188 0.7705
-1.000 0.1984 0.01078 0.00562 -0.0799 0.9137 0.8066
-0.750 0.2272 0.01059 0.00547 -0.0793 0.9052 0.8402
-0.500 0.2579 0.01036 0.00528 -0.0791 0.8983 0.8725
-0.250 0.2852 0.01014 0.00507 -0.0780 0.8896 0.9038
0.000 0.3150 0.00993 0.00487 -0.0775 0.8800 0.9356
0.250 0.3610 0.00967 0.00457 -0.0807 0.8733 0.9621
0.500 0.4108 0.00949 0.00435 -0.0850 0.8628 0.9855
0.750 0.4541 0.00933 0.00414 -0.0881 0.8511 1.0000
1.000 0.4794 0.00927 0.00400 -0.0876 0.8367 1.0000
1.250 0.5060 0.00925 0.00391 -0.0873 0.8218 1.0000
1.500 0.5331 0.00926 0.00385 -0.0870 0.8063 1.0000
1.750 0.5603 0.00929 0.00381 -0.0867 0.7902 1.0000
2.000 0.5875 0.00935 0.00379 -0.0864 0.7735 1.0000
2.250 0.6148 0.00943 0.00380 -0.0860 0.7564 1.0000
2.500 0.6406 0.00953 0.00386 -0.0855 0.7377 1.0000
2.750 0.6666 0.00965 0.00392 -0.0849 0.7184 1.0000
3.000 0.6928 0.00979 0.00398 -0.0844 0.6992 1.0000
3.250 0.7182 0.00994 0.00410 -0.0837 0.6781 1.0000
3.500 0.7435 0.01011 0.00420 -0.0830 0.6564 1.0000
3.750 0.7684 0.01030 0.00434 -0.0823 0.6337 1.0000
4.000 0.7932 0.01052 0.00447 -0.0815 0.6106 1.0000
4.250 0.8174 0.01075 0.00467 -0.0807 0.5856 1.0000
4.500 0.8413 0.01100 0.00487 -0.0798 0.5597 1.0000
4.750 0.8649 0.01129 0.00508 -0.0789 0.5330 1.0000
5.000 0.8880 0.01160 0.00532 -0.0779 0.5048 1.0000
5.250 0.9108 0.01194 0.00560 -0.0769 0.4753 1.0000
5.500 0.9330 0.01231 0.00590 -0.0758 0.4442 1.0000
5.750 0.9547 0.01273 0.00623 -0.0746 0.4111 1.0000
6.000 0.9755 0.01321 0.00659 -0.0734 0.3769 1.0000
6.250 0.9964 0.01371 0.00702 -0.0722 0.3414 1.0000
6.500 1.0164 0.01429 0.00749 -0.0709 0.3061 1.0000
6.750 1.0357 0.01494 0.00799 -0.0696 0.2663 1.0000
7.000 1.0538 0.01569 0.00855 -0.0682 0.2230 1.0000
7.250 1.0717 0.01651 0.00917 -0.0668 0.1822 1.0000
7.500 1.0893 0.01738 0.00987 -0.0654 0.1465 1.0000
7.750 1.1073 0.01824 0.01062 -0.0640 0.1174 1.0000
8.000 1.1242 0.01921 0.01146 -0.0625 0.0881 1.0000
8.250 1.1350 0.02080 0.01275 -0.0601 0.0500 1.0000
8.500 1.1430 0.02258 0.01445 -0.0571 0.0343 1.0000
8.750 1.1547 0.02388 0.01581 -0.0547 0.0297 1.0000
9.000 1.1596 0.02560 0.01760 -0.0514 0.0273 1.0000
9.250 1.1707 0.02688 0.01902 -0.0489 0.0258 1.0000
9.500 1.1815 0.02833 0.02057 -0.0466 0.0246 1.0000
9.750 1.1928 0.02987 0.02220 -0.0444 0.0236 1.0000
10.000 1.2047 0.03147 0.02387 -0.0425 0.0226 1.0000
10.250 1.2166 0.03354 0.02598 -0.0409 0.0214 1.0000
10.500 1.2321 0.03631 0.02890 -0.0398 0.0205 1.0000
10.750 1.2431 0.03798 0.03079 -0.0379 0.0199 1.0000
11.000 1.2543 0.04029 0.03336 -0.0362 0.0197 1.0000
11.250 1.2618 0.04286 0.03620 -0.0343 0.0194 1.0000
11.500 1.2653 0.04567 0.03930 -0.0322 0.0193 1.0000
11.750 1.2641 0.04871 0.04263 -0.0300 0.0193 1.0000
12.000 1.2584 0.05202 0.04624 -0.0279 0.0193 1.0000
12.250 1.2495 0.05562 0.05012 -0.0261 0.0194 1.0000
12.500 1.2372 0.05959 0.05437 -0.0249 0.0195 1.0000
12.750 1.2230 0.06394 0.05897 -0.0244 0.0196 1.0000
13.000 1.2067 0.06874 0.06402 -0.0246 0.0197 1.0000
13.250 1.1886 0.07410 0.06961 -0.0258 0.0198 1.0000
13.500 1.1694 0.08001 0.07573 -0.0278 0.0200 1.0000
13.750 1.1490 0.08660 0.08253 -0.0308 0.0201 1.0000
14.000 1.1280 0.09383 0.08994 -0.0347 0.0203 1.0000
14.250 1.1068 0.10177 0.09805 -0.0393 0.0204 1.0000
14.500 1.0852 0.11063 0.10703 -0.0444 0.0207 1.0000
14.750 0.9250 0.11587 0.11281 -0.0458 0.0211 1.0000
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Polar data table (+)
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