E209 (13.72%) (e209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 100,000 Max Cl/Cd: 50.82 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e209-il-100000.txt Download as CSV file: xf-e209-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3760 0.10006 0.09552 -0.0379 1.0000 0.1517
-10.250 -0.5544 0.07258 0.06768 -0.0577 1.0000 0.0665
-10.000 -0.5733 0.06735 0.06243 -0.0598 1.0000 0.0651
-9.750 -0.5995 0.06305 0.05809 -0.0604 1.0000 0.0639
-9.500 -0.6293 0.05949 0.05444 -0.0582 1.0000 0.0626
-9.250 -0.6583 0.05502 0.04973 -0.0557 1.0000 0.0606
-9.000 -0.6990 0.05053 0.04440 -0.0508 1.0000 0.0569
-8.750 -0.6985 0.04793 0.04149 -0.0481 1.0000 0.0563
-8.500 -0.6996 0.04482 0.03807 -0.0453 1.0000 0.0565
-8.250 -0.6982 0.04093 0.03394 -0.0429 1.0000 0.0572
-8.000 -0.6901 0.03831 0.03125 -0.0410 1.0000 0.0591
-7.750 -0.6804 0.03621 0.02900 -0.0388 1.0000 0.0605
-7.500 -0.6712 0.03396 0.02646 -0.0363 1.0000 0.0616
-7.250 -0.6604 0.03190 0.02413 -0.0338 1.0000 0.0630
-7.000 -0.6486 0.03028 0.02221 -0.0315 1.0000 0.0656
-6.750 -0.6369 0.02900 0.02057 -0.0290 1.0000 0.0688
-6.500 -0.6231 0.02714 0.01880 -0.0273 1.0000 0.0722
-6.250 -0.6098 0.02603 0.01762 -0.0253 1.0000 0.0763
-6.000 -0.5965 0.02512 0.01652 -0.0233 1.0000 0.0819
-5.750 -0.5719 0.02389 0.01543 -0.0237 0.9969 0.0912
-5.500 -0.5289 0.02228 0.01394 -0.0272 0.9877 0.1122
-5.250 -0.4891 0.02062 0.01263 -0.0304 0.9774 0.1596
-5.000 -0.4517 0.01894 0.01157 -0.0336 0.9664 0.2545
-4.750 -0.4137 0.01805 0.01145 -0.0363 0.9554 0.3930
-4.500 -0.3739 0.01820 0.01167 -0.0384 0.9432 0.4726
-4.250 -0.3363 0.01834 0.01177 -0.0399 0.9308 0.5175
-4.000 -0.2983 0.01844 0.01179 -0.0413 0.9194 0.5533
-3.750 -0.2508 0.01844 0.01171 -0.0443 0.9129 0.5867
-3.500 -0.2162 0.01840 0.01167 -0.0449 0.9009 0.6103
-3.250 -0.1809 0.01829 0.01144 -0.0459 0.8900 0.6339
-3.000 -0.1382 0.01809 0.01121 -0.0477 0.8830 0.6543
-2.750 -0.1078 0.01798 0.01105 -0.0476 0.8707 0.6723
-2.500 -0.0768 0.01785 0.01086 -0.0477 0.8593 0.6896
-2.250 -0.0435 0.01767 0.01060 -0.0481 0.8496 0.7063
-2.000 -0.0128 0.01752 0.01038 -0.0481 0.8391 0.7220
-1.750 0.0135 0.01745 0.01026 -0.0474 0.8272 0.7367
-1.500 0.0411 0.01736 0.01012 -0.0469 0.8166 0.7515
-1.250 0.0709 0.01723 0.00991 -0.0467 0.8075 0.7662
-1.000 0.0947 0.01722 0.00988 -0.0457 0.7959 0.7808
-0.750 0.1202 0.01720 0.00983 -0.0449 0.7859 0.7960
-0.500 0.1485 0.01713 0.00970 -0.0445 0.7773 0.8117
-0.250 0.1718 0.01719 0.00976 -0.0435 0.7666 0.8285
0.000 0.1991 0.01720 0.00974 -0.0430 0.7580 0.8463
0.250 0.2266 0.01724 0.00976 -0.0426 0.7488 0.8654
0.500 0.2575 0.01737 0.00989 -0.0429 0.7395 0.8842
0.750 0.2968 0.01742 0.00989 -0.0446 0.7318 0.9036
1.000 0.3353 0.01763 0.01011 -0.0468 0.7220 0.9251
1.250 0.3869 0.01771 0.01010 -0.0512 0.7145 0.9424
1.500 0.4416 0.01788 0.01027 -0.0569 0.7044 0.9590
1.750 0.4989 0.01796 0.01032 -0.0632 0.6955 0.9757
2.000 0.5574 0.01793 0.01026 -0.0698 0.6868 0.9933
2.250 0.5826 0.01809 0.01043 -0.0710 0.6778 1.0000
2.500 0.5947 0.01823 0.01050 -0.0688 0.6709 1.0000
2.750 0.6047 0.01866 0.01094 -0.0665 0.6623 1.0000
3.000 0.6248 0.01888 0.01111 -0.0652 0.6556 1.0000
3.250 0.6397 0.01939 0.01165 -0.0635 0.6468 1.0000
3.500 0.6633 0.01963 0.01183 -0.0626 0.6403 1.0000
3.750 0.6796 0.02019 0.01244 -0.0610 0.6312 1.0000
4.000 0.7053 0.02039 0.01261 -0.0603 0.6247 1.0000
4.250 0.7221 0.02096 0.01326 -0.0587 0.6151 1.0000
4.500 0.7492 0.02112 0.01338 -0.0583 0.6082 1.0000
4.750 0.7671 0.02164 0.01400 -0.0568 0.5981 1.0000
5.000 0.7899 0.02197 0.01437 -0.0558 0.5894 1.0000
5.250 0.8153 0.02213 0.01455 -0.0550 0.5805 1.0000
5.500 0.8352 0.02256 0.01508 -0.0537 0.5702 1.0000
5.750 0.8625 0.02262 0.01514 -0.0532 0.5614 1.0000
6.000 0.8856 0.02279 0.01539 -0.0521 0.5505 1.0000
6.250 0.9069 0.02305 0.01574 -0.0508 0.5390 1.0000
6.500 0.9316 0.02309 0.01585 -0.0499 0.5278 1.0000
6.750 0.9595 0.02291 0.01566 -0.0492 0.5164 1.0000
7.000 0.9847 0.02278 0.01558 -0.0482 0.5036 1.0000
7.250 1.0071 0.02274 0.01562 -0.0468 0.4894 1.0000
7.500 1.0301 0.02259 0.01555 -0.0455 0.4744 1.0000
7.750 1.0538 0.02236 0.01535 -0.0442 0.4583 1.0000
8.000 1.0720 0.02230 0.01543 -0.0422 0.4397 1.0000
8.250 1.0903 0.02218 0.01540 -0.0402 0.4192 1.0000
8.500 1.1081 0.02205 0.01530 -0.0380 0.3965 1.0000
8.750 1.1220 0.02208 0.01535 -0.0354 0.3692 1.0000
9.000 1.1309 0.02240 0.01570 -0.0322 0.3357 1.0000
9.250 1.1358 0.02300 0.01616 -0.0285 0.2974 1.0000
9.500 1.1358 0.02404 0.01700 -0.0245 0.2577 1.0000
9.750 1.1308 0.02540 0.01806 -0.0201 0.2249 1.0000
10.000 1.1245 0.02697 0.01942 -0.0157 0.1974 1.0000
10.250 1.1197 0.02871 0.02100 -0.0120 0.1735 1.0000
10.500 1.1156 0.03061 0.02270 -0.0089 0.1543 1.0000
10.750 1.1142 0.03257 0.02458 -0.0064 0.1368 1.0000
11.000 1.1142 0.03459 0.02654 -0.0042 0.1217 1.0000
11.250 1.1163 0.03667 0.02854 -0.0024 0.1086 1.0000
11.500 1.1212 0.03876 0.03054 -0.0009 0.0971 1.0000
11.750 1.1307 0.04083 0.03244 0.0004 0.0864 1.0000
12.000 1.1338 0.04295 0.03479 0.0018 0.0789 1.0000
12.250 1.1484 0.04510 0.03689 0.0028 0.0717 1.0000
12.500 1.1530 0.04728 0.03920 0.0038 0.0661 1.0000
12.750 1.1719 0.04978 0.04170 0.0046 0.0607 1.0000
13.000 1.1734 0.05232 0.04453 0.0057 0.0572 1.0000
13.250 1.1786 0.05467 0.04693 0.0063 0.0536 1.0000
13.500 1.1953 0.05827 0.05061 0.0069 0.0507 1.0000
13.750 1.1874 0.06169 0.05438 0.0077 0.0496 1.0000
14.000 1.1778 0.06545 0.05846 0.0080 0.0487 1.0000
14.250 1.1665 0.06953 0.06282 0.0078 0.0479 1.0000
14.500 1.1527 0.07393 0.06748 0.0072 0.0470 1.0000
14.750 1.1371 0.07874 0.07255 0.0061 0.0464 1.0000
15.000 1.1186 0.08417 0.07822 0.0043 0.0461 1.0000
15.250 1.0954 0.09051 0.08482 0.0017 0.0463 1.0000
15.500 1.0654 0.09852 0.09310 -0.0022 0.0475 1.0000
15.750 1.0360 0.10701 0.10181 -0.0069 0.0483 1.0000
16.000 1.0060 0.11649 0.11147 -0.0124 0.0493 1.0000
16.250 0.9792 0.12627 0.12137 -0.0182 0.0503 1.0000
16.500 0.9566 0.13611 0.13124 -0.0238 0.0511 1.0000
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Polar data table (+)
Polar graphs
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