E209 (13.72%) (e209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 50,000 Max Cl/Cd: 31.18 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e209-il-50000-n5.txt Download as CSV file: xf-e209-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4948 0.10128 0.09404 -0.0395 1.0000 0.0506
-11.250 -0.5064 0.09404 0.08690 -0.0432 1.0000 0.0504
-11.000 -0.5239 0.08622 0.07911 -0.0478 1.0000 0.0500
-10.750 -0.5443 0.07885 0.07175 -0.0523 1.0000 0.0492
-10.500 -0.5699 0.07185 0.06472 -0.0568 1.0000 0.0484
-10.250 -0.5956 0.06620 0.05898 -0.0597 1.0000 0.0476
-10.000 -0.6196 0.06201 0.05469 -0.0602 1.0000 0.0472
-9.750 -0.6418 0.05874 0.05129 -0.0584 1.0000 0.0475
-9.500 -0.6565 0.05556 0.04791 -0.0566 1.0000 0.0481
-9.250 -0.6666 0.05250 0.04460 -0.0545 1.0000 0.0489
-9.000 -0.6725 0.04949 0.04127 -0.0522 1.0000 0.0500
-8.750 -0.6741 0.04653 0.03790 -0.0499 1.0000 0.0512
-8.500 -0.6702 0.04373 0.03471 -0.0476 1.0000 0.0524
-8.250 -0.6596 0.04148 0.03242 -0.0459 1.0000 0.0540
-8.000 -0.6492 0.03977 0.03060 -0.0441 1.0000 0.0571
-7.750 -0.6381 0.03796 0.02854 -0.0421 1.0000 0.0609
-7.500 -0.6246 0.03607 0.02634 -0.0401 1.0000 0.0645
-7.250 -0.6109 0.03449 0.02482 -0.0382 1.0000 0.0679
-7.000 -0.5975 0.03314 0.02335 -0.0361 1.0000 0.0729
-6.750 -0.5853 0.03185 0.02199 -0.0339 1.0000 0.0793
-6.500 -0.5740 0.03071 0.02081 -0.0317 1.0000 0.0870
-6.250 -0.5638 0.02956 0.01967 -0.0293 1.0000 0.0949
-6.000 -0.5543 0.02852 0.01862 -0.0269 1.0000 0.1073
-5.750 -0.5454 0.02753 0.01769 -0.0247 1.0000 0.1230
-5.500 -0.5108 0.02604 0.01638 -0.0276 0.9884 0.1636
-5.250 -0.4774 0.02458 0.01528 -0.0304 0.9759 0.2254
-5.000 -0.4453 0.02348 0.01461 -0.0324 0.9628 0.3064
-4.750 -0.4131 0.02312 0.01455 -0.0336 0.9492 0.3884
-4.500 -0.3800 0.02309 0.01448 -0.0346 0.9356 0.4514
-4.250 -0.3464 0.02311 0.01438 -0.0354 0.9228 0.4975
-4.000 -0.3109 0.02311 0.01423 -0.0365 0.9115 0.5341
-3.750 -0.2767 0.02307 0.01406 -0.0373 0.8997 0.5645
-3.500 -0.2442 0.02300 0.01384 -0.0378 0.8874 0.5913
-3.250 -0.2117 0.02292 0.01365 -0.0381 0.8757 0.6139
-3.000 -0.1784 0.02279 0.01335 -0.0387 0.8650 0.6364
-2.750 -0.1450 0.02265 0.01310 -0.0392 0.8544 0.6558
-2.500 -0.1157 0.02254 0.01286 -0.0391 0.8422 0.6735
-2.250 -0.0858 0.02242 0.01263 -0.0391 0.8308 0.6906
-2.000 -0.0542 0.02228 0.01236 -0.0394 0.8207 0.7073
-1.750 -0.0244 0.02215 0.01212 -0.0395 0.8099 0.7234
-1.500 0.0027 0.02207 0.01195 -0.0391 0.7984 0.7391
-1.250 0.0315 0.02199 0.01178 -0.0390 0.7883 0.7549
-1.000 0.0620 0.02188 0.01157 -0.0392 0.7790 0.7709
-0.750 0.0880 0.02187 0.01151 -0.0387 0.7679 0.7876
-0.500 0.1171 0.02185 0.01144 -0.0388 0.7585 0.8051
-0.250 0.1491 0.02181 0.01134 -0.0392 0.7496 0.8226
0.000 0.1792 0.02188 0.01140 -0.0396 0.7395 0.8417
0.250 0.2151 0.02188 0.01134 -0.0409 0.7314 0.8621
0.500 0.2515 0.02198 0.01141 -0.0425 0.7217 0.8833
0.750 0.2925 0.02208 0.01148 -0.0452 0.7128 0.9048
1.000 0.3368 0.02214 0.01148 -0.0484 0.7045 0.9272
1.250 0.3814 0.02230 0.01162 -0.0522 0.6949 0.9499
1.500 0.4306 0.02231 0.01157 -0.0566 0.6874 0.9719
1.750 0.4769 0.02248 0.01175 -0.0611 0.6774 0.9966
2.000 0.4955 0.02270 0.01191 -0.0603 0.6695 1.0000
2.250 0.5108 0.02301 0.01218 -0.0587 0.6611 1.0000
2.500 0.5275 0.02339 0.01251 -0.0572 0.6530 1.0000
2.750 0.5474 0.02372 0.01280 -0.0561 0.6454 1.0000
3.000 0.5651 0.02418 0.01326 -0.0548 0.6370 1.0000
3.250 0.5876 0.02452 0.01359 -0.0540 0.6298 1.0000
3.500 0.6055 0.02507 0.01417 -0.0527 0.6214 1.0000
3.750 0.6297 0.02540 0.01449 -0.0521 0.6144 1.0000
4.000 0.6472 0.02603 0.01518 -0.0508 0.6057 1.0000
4.250 0.6727 0.02633 0.01553 -0.0503 0.5990 1.0000
4.500 0.6893 0.02704 0.01632 -0.0489 0.5898 1.0000
4.750 0.7166 0.02729 0.01660 -0.0486 0.5833 1.0000
5.000 0.7318 0.02807 0.01750 -0.0470 0.5734 1.0000
5.250 0.7569 0.02840 0.01791 -0.0464 0.5659 1.0000
5.500 0.7756 0.02900 0.01862 -0.0452 0.5562 1.0000
5.750 0.7946 0.02960 0.01933 -0.0440 0.5466 1.0000
6.000 0.8230 0.02968 0.01948 -0.0435 0.5384 1.0000
6.250 0.8379 0.03040 0.02039 -0.0418 0.5269 1.0000
6.500 0.8569 0.03090 0.02102 -0.0405 0.5161 1.0000
6.750 0.8822 0.03101 0.02123 -0.0396 0.5059 1.0000
7.000 0.9045 0.03122 0.02157 -0.0384 0.4944 1.0000
7.250 0.9212 0.03166 0.02220 -0.0367 0.4813 1.0000
7.500 0.9391 0.03198 0.02268 -0.0350 0.4679 1.0000
7.750 0.9574 0.03219 0.02304 -0.0332 0.4536 1.0000
8.000 0.9755 0.03233 0.02331 -0.0314 0.4384 1.0000
8.250 0.9935 0.03239 0.02350 -0.0295 0.4221 1.0000
8.500 1.0107 0.03242 0.02366 -0.0274 0.4047 1.0000
8.750 1.0175 0.03304 0.02445 -0.0246 0.3851 1.0000
9.000 1.0278 0.03340 0.02490 -0.0219 0.3645 1.0000
9.250 1.0337 0.03397 0.02554 -0.0189 0.3426 1.0000
9.500 1.0379 0.03463 0.02620 -0.0158 0.3195 1.0000
9.750 1.0387 0.03572 0.02730 -0.0129 0.2951 1.0000
10.000 1.0396 0.03697 0.02848 -0.0103 0.2703 1.0000
10.250 1.0390 0.03853 0.02994 -0.0080 0.2465 1.0000
10.500 1.0359 0.04058 0.03192 -0.0062 0.2239 1.0000
10.750 1.0328 0.04282 0.03401 -0.0046 0.2043 1.0000
11.000 1.0294 0.04535 0.03647 -0.0035 0.1860 1.0000
11.250 1.0260 0.04804 0.03912 -0.0027 0.1693 1.0000
11.500 1.0236 0.05079 0.04182 -0.0020 0.1549 1.0000
11.750 1.0212 0.05364 0.04464 -0.0016 0.1416 1.0000
12.000 1.0195 0.05653 0.04749 -0.0012 0.1299 1.0000
12.250 1.0189 0.05935 0.05024 -0.0009 0.1197 1.0000
12.500 1.0184 0.06235 0.05334 -0.0009 0.1097 1.0000
12.750 1.0188 0.06536 0.05642 -0.0008 0.1011 1.0000
13.000 1.0207 0.06806 0.05900 -0.0006 0.0940 1.0000
13.250 1.0204 0.07144 0.06269 -0.0009 0.0868 1.0000
13.500 1.0234 0.07416 0.06530 -0.0008 0.0809 1.0000
13.750 1.0220 0.07795 0.06940 -0.0014 0.0756 1.0000
14.000 1.0232 0.08107 0.07255 -0.0018 0.0708 1.0000
14.250 1.0242 0.08463 0.07626 -0.0022 0.0671 1.0000
14.500 1.0187 0.08936 0.08129 -0.0035 0.0640 1.0000
14.750 1.0139 0.09387 0.08596 -0.0049 0.0613 1.0000
15.000 1.0209 0.09615 0.08808 -0.0050 0.0575 1.0000
15.250 1.0064 0.10271 0.09499 -0.0079 0.0564 1.0000
15.500 0.9891 0.11014 0.10271 -0.0116 0.0556 1.0000
15.750 0.9685 0.11864 0.11146 -0.0161 0.0553 1.0000
16.000 0.9424 0.12910 0.12213 -0.0221 0.0554 1.0000
16.250 0.9132 0.14142 0.13456 -0.0293 0.0559 1.0000
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Polar data table (+)
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