E209 (13.72%) (e209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 50,000 Max Cl/Cd: 29.39 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e209-il-50000.txt Download as CSV file: xf-e209-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3855 0.10888 0.10183 -0.0178 1.0000 0.3044
-9.500 -0.4970 0.08481 0.07816 -0.0441 1.0000 0.1389
-9.250 -0.5145 0.07783 0.07125 -0.0479 1.0000 0.1326
-9.000 -0.6098 0.06984 0.06321 -0.0518 1.0000 0.1224
-8.750 -0.6099 0.06552 0.05889 -0.0508 1.0000 0.1210
-8.500 -0.6193 0.06136 0.05462 -0.0495 1.0000 0.1194
-8.250 -0.6304 0.05726 0.05034 -0.0479 1.0000 0.1178
-8.000 -0.6396 0.05324 0.04605 -0.0458 1.0000 0.1166
-7.750 -0.6435 0.04963 0.04211 -0.0436 1.0000 0.1165
-7.500 -0.6436 0.04638 0.03849 -0.0413 1.0000 0.1182
-7.250 -0.6414 0.04337 0.03499 -0.0388 1.0000 0.1207
-7.000 -0.6353 0.04048 0.03164 -0.0364 1.0000 0.1233
-6.750 -0.6210 0.03795 0.02912 -0.0346 1.0000 0.1278
-6.500 -0.6092 0.03584 0.02667 -0.0324 1.0000 0.1343
-6.250 -0.5957 0.03387 0.02463 -0.0305 1.0000 0.1433
-6.000 -0.5811 0.03189 0.02243 -0.0285 1.0000 0.1538
-5.750 -0.5669 0.03032 0.02091 -0.0266 1.0000 0.1702
-5.500 -0.5530 0.02879 0.01937 -0.0245 1.0000 0.1935
-5.250 -0.5404 0.02729 0.01815 -0.0224 1.0000 0.2275
-5.000 -0.5295 0.02598 0.01727 -0.0201 1.0000 0.2778
-4.750 -0.5204 0.02511 0.01700 -0.0173 1.0000 0.3477
-4.500 -0.5125 0.02517 0.01755 -0.0136 1.0000 0.4242
-4.250 -0.5046 0.02559 0.01821 -0.0096 1.0000 0.4920
-4.000 -0.4963 0.02605 0.01878 -0.0055 1.0000 0.5446
-3.750 -0.4879 0.02644 0.01922 -0.0015 1.0000 0.5893
-3.500 -0.4798 0.02680 0.01963 0.0028 1.0000 0.6266
-3.250 -0.4713 0.02699 0.01979 0.0065 1.0000 0.6624
-3.000 -0.4597 0.02719 0.01994 0.0097 0.9986 0.6966
-2.750 -0.4270 0.02790 0.02054 0.0100 0.9864 0.7352
-2.500 -0.3959 0.02835 0.02084 0.0099 0.9745 0.7715
-2.250 -0.3663 0.02870 0.02106 0.0100 0.9631 0.8037
-2.000 -0.3331 0.02907 0.02127 0.0095 0.9518 0.8347
-1.750 -0.2894 0.02958 0.02161 0.0070 0.9415 0.8652
-1.500 -0.2371 0.03011 0.02193 0.0025 0.9306 0.8933
-1.250 -0.1581 0.03089 0.02245 -0.0072 0.9207 0.9183
-1.000 -0.0575 0.03156 0.02279 -0.0215 0.9118 0.9404
-0.750 0.0341 0.03181 0.02281 -0.0348 0.9015 0.9593
-0.500 0.1192 0.03184 0.02266 -0.0474 0.8918 0.9784
-0.250 0.2217 0.03146 0.02212 -0.0629 0.8836 0.9963
0.000 0.2360 0.03158 0.02218 -0.0637 0.8713 1.0000
0.250 0.2281 0.03180 0.02236 -0.0608 0.8591 1.0000
0.500 0.2172 0.03195 0.02245 -0.0574 0.8479 1.0000
0.750 0.2179 0.03210 0.02250 -0.0553 0.8382 1.0000
1.000 0.1999 0.03270 0.02293 -0.0501 0.8272 1.0000
1.250 0.2178 0.03340 0.02348 -0.0499 0.8182 1.0000
1.500 0.2408 0.03413 0.02409 -0.0503 0.8092 1.0000
1.750 0.2502 0.03510 0.02496 -0.0489 0.7998 1.0000
2.000 0.2897 0.03578 0.02557 -0.0514 0.7920 1.0000
2.250 0.2882 0.03703 0.02672 -0.0485 0.7825 1.0000
2.500 0.3179 0.03792 0.02757 -0.0496 0.7744 1.0000
2.750 0.3266 0.03914 0.02875 -0.0482 0.7657 1.0000
3.000 0.3470 0.04026 0.02983 -0.0482 0.7575 1.0000
3.250 0.3649 0.04144 0.03099 -0.0479 0.7491 1.0000
3.500 0.3774 0.04280 0.03232 -0.0470 0.7408 1.0000
3.750 0.4038 0.04390 0.03343 -0.0477 0.7325 1.0000
4.000 0.4078 0.04551 0.03504 -0.0460 0.7241 1.0000
4.250 0.4483 0.04641 0.03599 -0.0480 0.7154 1.0000
4.500 0.4394 0.04836 0.03791 -0.0453 0.7067 1.0000
4.750 0.4649 0.04965 0.03924 -0.0457 0.6975 1.0000
5.000 0.4785 0.05117 0.04081 -0.0451 0.6879 1.0000
5.250 0.4871 0.05290 0.04257 -0.0442 0.6784 1.0000
5.500 0.5151 0.05414 0.04389 -0.0446 0.6675 1.0000
5.750 0.5320 0.05565 0.04546 -0.0443 0.6564 1.0000
6.000 0.5361 0.05758 0.04746 -0.0431 0.6453 1.0000
6.250 0.5530 0.05917 0.04912 -0.0426 0.6331 1.0000
6.500 0.5745 0.06058 0.05063 -0.0424 0.6199 1.0000
6.750 0.5969 0.06193 0.05208 -0.0421 0.6059 1.0000
7.000 0.6186 0.06326 0.05354 -0.0416 0.5915 1.0000
7.250 0.6368 0.06467 0.05506 -0.0409 0.5762 1.0000
7.500 0.6526 0.06617 0.05668 -0.0401 0.5606 1.0000
7.750 0.6661 0.06777 0.05839 -0.0391 0.5443 1.0000
8.000 0.6797 0.06936 0.06011 -0.0381 0.5273 1.0000
8.250 0.6972 0.07066 0.06154 -0.0371 0.5097 1.0000
8.500 0.7324 0.07048 0.06157 -0.0358 0.4906 1.0000
8.750 0.7667 0.07003 0.06136 -0.0341 0.4714 1.0000
9.000 0.7645 0.07268 0.06408 -0.0330 0.4530 1.0000
9.250 0.7963 0.07191 0.06353 -0.0309 0.4323 1.0000
9.500 0.8451 0.06864 0.06058 -0.0276 0.4105 1.0000
9.750 1.1138 0.03889 0.03142 -0.0220 0.3315 1.0000
10.000 1.1288 0.03841 0.03062 -0.0184 0.2920 1.0000
10.250 1.1334 0.03936 0.03131 -0.0149 0.2592 1.0000
10.500 1.1380 0.04089 0.03258 -0.0117 0.2301 1.0000
10.750 1.1431 0.04281 0.03430 -0.0089 0.2051 1.0000
11.000 1.1574 0.04505 0.03622 -0.0073 0.1804 1.0000
11.250 1.1612 0.04762 0.03885 -0.0050 0.1643 1.0000
11.500 1.1677 0.05033 0.04159 -0.0030 0.1499 1.0000
11.750 1.1785 0.05332 0.04461 -0.0017 0.1374 1.0000
12.000 1.1763 0.05617 0.04766 0.0006 0.1294 1.0000
12.250 1.1769 0.05968 0.05134 0.0022 0.1232 1.0000
12.500 1.1606 0.06335 0.05535 0.0044 0.1206 1.0000
12.750 1.1795 0.06682 0.05872 0.0047 0.1119 1.0000
13.000 1.1560 0.07084 0.06307 0.0063 0.1113 1.0000
13.250 1.1309 0.07553 0.06804 0.0067 0.1111 1.0000
13.500 1.1050 0.08089 0.07364 0.0061 0.1113 1.0000
13.750 1.0774 0.08704 0.07999 0.0045 0.1117 1.0000
14.000 1.0508 0.09386 0.08697 0.0021 0.1123 1.0000
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Polar data table (+)
Polar graphs
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