E209 (13.72%) (e209-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 200,000 Max Cl/Cd: 71.76 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e209-il-200000.txt Download as CSV file: xf-e209-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E209 (13.72%)
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5378 0.08253 0.07892 -0.0489 1.0000 0.0352
-11.250 -0.5612 0.07420 0.07056 -0.0542 1.0000 0.0342
-11.000 -0.5926 0.06596 0.06222 -0.0602 1.0000 0.0336
-10.750 -0.6218 0.05964 0.05579 -0.0642 1.0000 0.0327
-10.500 -0.6527 0.05469 0.05068 -0.0657 1.0000 0.0323
-10.250 -0.6907 0.05066 0.04644 -0.0631 1.0000 0.0312
-10.000 -0.7456 0.04606 0.04111 -0.0563 1.0000 0.0290
-9.750 -0.7450 0.04464 0.03948 -0.0535 1.0000 0.0287
-9.500 -0.7489 0.04157 0.03615 -0.0505 1.0000 0.0286
-9.250 -0.7514 0.03881 0.03310 -0.0473 1.0000 0.0287
-9.000 -0.7501 0.03590 0.02989 -0.0445 1.0000 0.0287
-8.750 -0.7472 0.03244 0.02619 -0.0418 1.0000 0.0294
-8.500 -0.7370 0.03092 0.02465 -0.0399 1.0000 0.0308
-8.250 -0.7261 0.02950 0.02311 -0.0376 1.0000 0.0317
-8.000 -0.7153 0.02797 0.02140 -0.0352 1.0000 0.0326
-7.750 -0.7040 0.02645 0.01969 -0.0327 1.0000 0.0333
-7.500 -0.6923 0.02514 0.01821 -0.0303 1.0000 0.0344
-7.250 -0.6621 0.02385 0.01666 -0.0312 0.9968 0.0360
-7.000 -0.6248 0.02185 0.01466 -0.0340 0.9916 0.0396
-6.750 -0.5839 0.02070 0.01343 -0.0370 0.9854 0.0436
-6.500 -0.5467 0.01922 0.01191 -0.0394 0.9783 0.0481
-6.250 -0.5055 0.01827 0.01093 -0.0424 0.9717 0.0553
-6.000 -0.4707 0.01701 0.00970 -0.0443 0.9619 0.0656
-5.750 -0.4332 0.01568 0.00849 -0.0468 0.9543 0.0932
-5.500 -0.3980 0.01441 0.00755 -0.0490 0.9447 0.1488
-5.250 -0.3642 0.01339 0.00686 -0.0508 0.9340 0.2168
-5.000 -0.3303 0.01246 0.00628 -0.0524 0.9234 0.3016
-4.750 -0.2956 0.01187 0.00603 -0.0539 0.9126 0.3948
-4.500 -0.2619 0.01170 0.00587 -0.0548 0.8984 0.4492
-4.250 -0.2289 0.01158 0.00567 -0.0555 0.8832 0.4802
-4.000 -0.1984 0.01150 0.00553 -0.0556 0.8663 0.5024
-3.750 -0.1698 0.01147 0.00539 -0.0554 0.8485 0.5227
-3.500 -0.1424 0.01148 0.00526 -0.0549 0.8313 0.5414
-3.250 -0.1155 0.01149 0.00517 -0.0544 0.8151 0.5577
-3.000 -0.0889 0.01150 0.00508 -0.0539 0.7999 0.5726
-2.750 -0.0623 0.01151 0.00499 -0.0534 0.7858 0.5863
-2.500 -0.0358 0.01151 0.00492 -0.0529 0.7727 0.5990
-2.250 -0.0090 0.01151 0.00484 -0.0524 0.7608 0.6116
-2.000 0.0172 0.01151 0.00478 -0.0519 0.7484 0.6241
-1.750 0.0437 0.01152 0.00472 -0.0515 0.7370 0.6366
-1.500 0.0705 0.01154 0.00466 -0.0512 0.7270 0.6494
-1.250 0.0971 0.01153 0.00462 -0.0508 0.7171 0.6612
-1.000 0.1236 0.01153 0.00461 -0.0504 0.7071 0.6734
-0.750 0.1505 0.01154 0.00458 -0.0501 0.6987 0.6862
-0.500 0.1769 0.01153 0.00457 -0.0497 0.6893 0.6994
-0.250 0.2036 0.01155 0.00457 -0.0494 0.6811 0.7134
0.000 0.2302 0.01154 0.00458 -0.0490 0.6728 0.7282
0.250 0.2565 0.01155 0.00461 -0.0486 0.6650 0.7439
0.500 0.2828 0.01155 0.00464 -0.0482 0.6573 0.7610
0.750 0.3085 0.01156 0.00471 -0.0476 0.6498 0.7803
1.000 0.3343 0.01157 0.00476 -0.0470 0.6424 0.8031
1.250 0.3595 0.01159 0.00487 -0.0462 0.6355 0.8275
1.500 0.3849 0.01161 0.00496 -0.0454 0.6282 0.8563
1.750 0.4132 0.01169 0.00509 -0.0451 0.6218 0.8873
2.000 0.4472 0.01178 0.00524 -0.0461 0.6140 0.9176
2.250 0.4880 0.01194 0.00535 -0.0485 0.6075 0.9438
2.500 0.5324 0.01206 0.00551 -0.0520 0.5993 0.9645
2.750 0.5800 0.01222 0.00560 -0.0561 0.5925 0.9796
3.000 0.6291 0.01231 0.00573 -0.0608 0.5839 0.9929
3.250 0.6676 0.01243 0.00578 -0.0634 0.5774 1.0000
3.500 0.6853 0.01255 0.00594 -0.0618 0.5698 1.0000
3.750 0.7075 0.01271 0.00603 -0.0608 0.5636 1.0000
4.000 0.7275 0.01285 0.00624 -0.0595 0.5553 1.0000
4.250 0.7512 0.01301 0.00631 -0.0587 0.5485 1.0000
4.500 0.7722 0.01316 0.00655 -0.0575 0.5398 1.0000
4.750 0.7966 0.01331 0.00663 -0.0568 0.5327 1.0000
5.000 0.8179 0.01345 0.00685 -0.0556 0.5235 1.0000
5.250 0.8417 0.01359 0.00699 -0.0547 0.5156 1.0000
5.500 0.8644 0.01370 0.00715 -0.0537 0.5062 1.0000
5.750 0.8872 0.01384 0.00733 -0.0527 0.4967 1.0000
6.000 0.9115 0.01395 0.00741 -0.0520 0.4876 1.0000
6.250 0.9335 0.01405 0.00760 -0.0508 0.4764 1.0000
6.500 0.9560 0.01417 0.00779 -0.0498 0.4652 1.0000
6.750 0.9785 0.01427 0.00793 -0.0487 0.4533 1.0000
7.000 1.0008 0.01439 0.00808 -0.0476 0.4407 1.0000
7.250 1.0224 0.01452 0.00825 -0.0464 0.4265 1.0000
7.500 1.0432 0.01466 0.00847 -0.0451 0.4104 1.0000
7.750 1.0634 0.01484 0.00871 -0.0437 0.3916 1.0000
8.000 1.0821 0.01508 0.00894 -0.0421 0.3701 1.0000
8.250 1.0994 0.01541 0.00926 -0.0403 0.3426 1.0000
8.500 1.1140 0.01589 0.00967 -0.0381 0.3087 1.0000
8.750 1.1251 0.01660 0.01022 -0.0356 0.2685 1.0000
9.000 1.1326 0.01755 0.01096 -0.0326 0.2272 1.0000
9.250 1.1376 0.01864 0.01185 -0.0294 0.1915 1.0000
9.500 1.1404 0.01974 0.01280 -0.0258 0.1627 1.0000
9.750 1.1404 0.02093 0.01384 -0.0219 0.1399 1.0000
10.000 1.1424 0.02213 0.01497 -0.0186 0.1199 1.0000
10.250 1.1429 0.02349 0.01626 -0.0155 0.1039 1.0000
10.500 1.1428 0.02499 0.01774 -0.0126 0.0904 1.0000
10.750 1.1429 0.02662 0.01936 -0.0101 0.0795 1.0000
11.000 1.1410 0.02853 0.02125 -0.0079 0.0708 1.0000
11.250 1.1392 0.03060 0.02330 -0.0061 0.0635 1.0000
11.500 1.1411 0.03255 0.02533 -0.0047 0.0567 1.0000
11.750 1.1372 0.03508 0.02782 -0.0034 0.0519 1.0000
12.000 1.1409 0.03710 0.02996 -0.0025 0.0470 1.0000
12.250 1.1423 0.03937 0.03226 -0.0018 0.0437 1.0000
12.500 1.1401 0.04207 0.03495 -0.0008 0.0406 1.0000
12.750 1.1449 0.04419 0.03721 -0.0004 0.0375 1.0000
13.000 1.1473 0.04655 0.03962 0.0000 0.0351 1.0000
13.250 1.1478 0.04916 0.04220 0.0009 0.0325 1.0000
13.500 1.1526 0.05144 0.04465 0.0012 0.0308 1.0000
13.750 1.1571 0.05379 0.04710 0.0016 0.0291 1.0000
14.000 1.1615 0.05615 0.04952 0.0019 0.0277 1.0000
14.250 1.1675 0.05844 0.05180 0.0024 0.0265 1.0000
14.500 1.1739 0.06106 0.05454 0.0033 0.0253 1.0000
14.750 1.1727 0.06418 0.05788 0.0028 0.0242 1.0000
15.000 1.1735 0.06728 0.06115 0.0024 0.0234 1.0000
15.250 1.1738 0.07048 0.06450 0.0020 0.0227 1.0000
15.500 1.1728 0.07384 0.06798 0.0012 0.0220 1.0000
15.750 1.1717 0.07736 0.07164 0.0004 0.0214 1.0000
16.000 1.1704 0.08100 0.07538 -0.0004 0.0209 1.0000
16.250 1.1674 0.08503 0.07955 -0.0014 0.0206 1.0000
16.500 1.1612 0.08973 0.08441 -0.0027 0.0203 1.0000
16.750 1.1507 0.09516 0.09004 -0.0047 0.0202 1.0000
17.000 1.1364 0.10133 0.09643 -0.0074 0.0201 1.0000
17.250 1.1219 0.10770 0.10301 -0.0107 0.0201 1.0000
17.500 1.1056 0.11467 0.11018 -0.0145 0.0201 1.0000
17.750 1.0880 0.12219 0.11791 -0.0190 0.0202 1.0000
18.000 1.0677 0.13073 0.12667 -0.0245 0.0203 1.0000
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Polar data table (+)
Polar graphs
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