EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 50,000 Max Cl/Cd: 26.15 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e338-il-50000-n5.txt Download as CSV file: xf-e338-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 338 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3382 0.11346 0.10692 -0.0254 1.0000 0.1080
-9.500 -0.3599 0.11165 0.10527 -0.0304 1.0000 0.1099
-9.250 -0.3573 0.10754 0.10127 -0.0314 1.0000 0.1108
-9.000 -0.3352 0.10299 0.09674 -0.0287 1.0000 0.1133
-8.750 -0.3295 0.09959 0.09341 -0.0288 1.0000 0.1156
-8.500 -0.3292 0.09632 0.09024 -0.0297 1.0000 0.1180
-8.250 -0.3341 0.09313 0.08716 -0.0311 1.0000 0.1208
-8.000 -0.3954 0.09301 0.08722 -0.0338 1.0000 0.1262
-7.750 -0.3811 0.08810 0.08246 -0.0328 1.0000 0.1277
-7.250 -0.3111 0.06472 0.05947 -0.0410 0.9707 0.0534
-6.750 -0.3844 0.07036 0.06460 -0.0334 0.9812 0.0520
-6.250 -0.3468 0.06006 0.05359 -0.0396 0.9244 0.0441
-6.000 -0.3208 0.05593 0.04920 -0.0422 0.9034 0.0429
-5.750 -0.2970 0.05211 0.04501 -0.0436 0.8821 0.0420
-5.500 -0.2746 0.04868 0.04115 -0.0441 0.8611 0.0419
-5.250 -0.2521 0.04574 0.03776 -0.0440 0.8411 0.0423
-5.000 -0.2305 0.04308 0.03461 -0.0433 0.8223 0.0427
-4.750 -0.2090 0.04069 0.03168 -0.0421 0.8046 0.0434
-4.500 -0.1870 0.03852 0.02901 -0.0407 0.7876 0.0436
-4.250 -0.1640 0.03648 0.02650 -0.0394 0.7713 0.0437
-4.000 -0.1393 0.03456 0.02411 -0.0381 0.7557 0.0441
-3.750 -0.1126 0.03284 0.02192 -0.0371 0.7408 0.0448
-3.500 -0.0855 0.03132 0.02021 -0.0366 0.7265 0.0471
-3.250 -0.0565 0.03011 0.01878 -0.0363 0.7130 0.0510
-3.000 -0.0208 0.02881 0.01708 -0.0366 0.7002 0.0547
-2.750 0.0177 0.02757 0.01572 -0.0378 0.6881 0.0613
-2.500 0.0496 0.02667 0.01466 -0.0379 0.6755 0.0695
-2.000 0.2839 0.02257 0.01275 -0.0646 0.6459 1.0000
-1.750 0.3056 0.02261 0.01243 -0.0637 0.6361 1.0000
-1.500 0.3272 0.02268 0.01223 -0.0629 0.6256 1.0000
-1.250 0.3489 0.02278 0.01206 -0.0620 0.6162 1.0000
-1.000 0.3709 0.02289 0.01191 -0.0611 0.6074 1.0000
-0.750 0.3927 0.02305 0.01188 -0.0604 0.5984 1.0000
-0.500 0.4152 0.02318 0.01178 -0.0596 0.5906 1.0000
-0.250 0.4372 0.02340 0.01185 -0.0588 0.5821 1.0000
0.000 0.4595 0.02358 0.01185 -0.0580 0.5749 1.0000
0.250 0.4813 0.02383 0.01198 -0.0573 0.5674 1.0000
0.500 0.5031 0.02407 0.01209 -0.0564 0.5601 1.0000
0.750 0.5251 0.02432 0.01220 -0.0556 0.5537 1.0000
1.000 0.5460 0.02467 0.01249 -0.0547 0.5463 1.0000
1.250 0.5682 0.02490 0.01258 -0.0538 0.5409 1.0000
1.500 0.5882 0.02534 0.01300 -0.0528 0.5339 1.0000
1.750 0.6092 0.02570 0.01329 -0.0518 0.5278 1.0000
2.000 0.6311 0.02599 0.01347 -0.0509 0.5230 1.0000
2.250 0.6494 0.02658 0.01410 -0.0498 0.5159 1.0000
2.500 0.6702 0.02695 0.01442 -0.0487 0.5106 1.0000
2.750 0.6907 0.02738 0.01479 -0.0477 0.5057 1.0000
3.000 0.7079 0.02804 0.01554 -0.0464 0.4992 1.0000
3.250 0.7282 0.02846 0.01592 -0.0453 0.4943 1.0000
3.500 0.7480 0.02895 0.01639 -0.0441 0.4897 1.0000
3.750 0.7628 0.02977 0.01731 -0.0426 0.4833 1.0000
4.000 0.7821 0.03026 0.01782 -0.0413 0.4786 1.0000
4.250 0.8026 0.03069 0.01821 -0.0402 0.4746 1.0000
4.500 0.8128 0.03181 0.01949 -0.0382 0.4681 1.0000
4.750 0.8302 0.03240 0.02011 -0.0367 0.4633 1.0000
5.000 0.8524 0.03271 0.02037 -0.0357 0.4596 1.0000
5.250 0.8566 0.03416 0.02205 -0.0330 0.4530 1.0000
5.500 0.8708 0.03492 0.02287 -0.0312 0.4481 1.0000
5.750 0.8925 0.03524 0.02317 -0.0301 0.4443 1.0000
6.000 0.8920 0.03688 0.02500 -0.0270 0.4379 1.0000
6.250 0.9010 0.03791 0.02612 -0.0247 0.4327 1.0000
6.500 0.9221 0.03822 0.02647 -0.0234 0.4290 1.0000
6.750 0.9136 0.04020 0.02861 -0.0195 0.4225 1.0000
7.000 0.9160 0.04152 0.03003 -0.0166 0.4170 1.0000
7.250 0.9380 0.04174 0.03027 -0.0154 0.4133 1.0000
7.500 0.9070 0.04484 0.03351 -0.0096 0.4057 1.0000
7.750 0.9078 0.04619 0.03492 -0.0067 0.4004 1.0000
8.000 0.9375 0.04595 0.03474 -0.0061 0.3972 1.0000
8.250 0.8481 0.05244 0.04122 0.0030 0.3862 1.0000
8.500 0.8764 0.05216 0.04102 0.0039 0.3828 1.0000
9.000 0.8347 0.05960 0.04852 0.0077 0.3669 1.0000
9.500 0.8176 0.06649 0.05549 0.0086 0.3512 1.0000
10.000 0.8089 0.07272 0.06183 0.0092 0.3361 1.0000
10.250 0.7814 0.07866 0.06777 0.0083 0.3251 1.0000
10.500 0.8040 0.07880 0.06801 0.0093 0.3213 1.0000
10.750 0.7818 0.08431 0.07354 0.0083 0.3111 1.0000
11.000 0.8018 0.08477 0.07413 0.0092 0.3069 1.0000
11.250 0.7849 0.08978 0.07918 0.0082 0.2972 1.0000
11.500 0.8032 0.09045 0.07995 0.0089 0.2926 1.0000
12.000 0.8054 0.09620 0.08586 0.0083 0.2785 1.0000
12.250 0.7941 0.10086 0.09056 0.0071 0.2700 1.0000
12.500 0.8074 0.10221 0.09205 0.0074 0.2647 1.0000
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Polar data table (+)
Polar graphs
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