EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 50,000 Max Cl/Cd: 24.13 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e342-il-50000-n5.txt Download as CSV file: xf-e342-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 342 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3509 0.10178 0.09562 -0.0253 1.0000 0.1219
-9.000 -0.3531 0.09792 0.09186 -0.0270 1.0000 0.1224
-8.500 -0.3869 0.08244 0.07630 -0.0379 1.0000 0.0527
-8.250 -0.3939 0.07922 0.07315 -0.0370 1.0000 0.0512
-8.000 -0.4074 0.07626 0.07025 -0.0352 1.0000 0.0499
-7.750 -0.4423 0.07256 0.06634 -0.0320 1.0000 0.0463
-7.500 -0.4424 0.07010 0.06401 -0.0299 1.0000 0.0457
-7.250 -0.4478 0.06770 0.06168 -0.0274 0.9962 0.0451
-7.000 -0.4300 0.06309 0.05687 -0.0302 0.9533 0.0439
-6.750 -0.4101 0.05862 0.05206 -0.0325 0.9191 0.0426
-6.500 -0.3903 0.05413 0.04709 -0.0339 0.8915 0.0414
-6.250 -0.3719 0.05003 0.04236 -0.0338 0.8662 0.0403
-6.000 -0.3530 0.04666 0.03830 -0.0328 0.8433 0.0396
-5.750 -0.3338 0.04404 0.03522 -0.0316 0.8204 0.0395
-5.500 -0.3147 0.04169 0.03247 -0.0302 0.7997 0.0400
-5.250 -0.2946 0.03986 0.03035 -0.0290 0.7806 0.0413
-5.000 -0.2739 0.03809 0.02818 -0.0275 0.7628 0.0431
-4.750 -0.2511 0.03627 0.02586 -0.0260 0.7463 0.0447
-4.500 -0.2250 0.03441 0.02343 -0.0248 0.7310 0.0462
-4.250 -0.1960 0.03272 0.02153 -0.0246 0.7165 0.0477
-4.000 -0.1642 0.03129 0.01985 -0.0247 0.7026 0.0509
-3.750 -0.1271 0.02993 0.01824 -0.0255 0.6889 0.0562
-3.500 -0.0836 0.02873 0.01676 -0.0274 0.6749 0.0631
-3.250 -0.0473 0.02771 0.01561 -0.0284 0.6625 0.0743
-3.000 -0.0187 0.02678 0.01462 -0.0282 0.6520 0.0890
-2.750 0.0760 0.02347 0.01471 -0.0367 0.6379 0.7733
-2.500 0.2458 0.02463 0.01450 -0.0578 0.6188 1.0000
-2.250 0.2670 0.02459 0.01421 -0.0572 0.6087 1.0000
-2.000 0.2883 0.02457 0.01387 -0.0564 0.6005 1.0000
-1.750 0.3097 0.02460 0.01373 -0.0558 0.5911 1.0000
-1.500 0.3312 0.02463 0.01349 -0.0549 0.5836 1.0000
-1.250 0.3525 0.02473 0.01343 -0.0543 0.5750 1.0000
-1.000 0.3741 0.02481 0.01331 -0.0535 0.5677 1.0000
-0.750 0.3960 0.02496 0.01330 -0.0528 0.5605 1.0000
-0.500 0.4179 0.02512 0.01333 -0.0522 0.5534 1.0000
-0.250 0.4400 0.02524 0.01324 -0.0514 0.5478 1.0000
0.000 0.4614 0.02553 0.01348 -0.0508 0.5402 1.0000
0.250 0.4832 0.02573 0.01356 -0.0500 0.5342 1.0000
0.500 0.5049 0.02596 0.01364 -0.0492 0.5289 1.0000
0.750 0.5258 0.02633 0.01401 -0.0485 0.5222 1.0000
1.000 0.5473 0.02659 0.01417 -0.0477 0.5168 1.0000
1.250 0.5690 0.02686 0.01432 -0.0468 0.5122 1.0000
1.500 0.5888 0.02736 0.01486 -0.0460 0.5056 1.0000
1.750 0.6098 0.02771 0.01515 -0.0451 0.5007 1.0000
2.000 0.6317 0.02798 0.01532 -0.0442 0.4968 1.0000
2.250 0.6503 0.02862 0.01603 -0.0434 0.4908 1.0000
2.500 0.6699 0.02913 0.01655 -0.0424 0.4856 1.0000
2.750 0.6909 0.02947 0.01684 -0.0414 0.4814 1.0000
3.000 0.7104 0.03002 0.01740 -0.0404 0.4772 1.0000
3.250 0.7267 0.03085 0.01834 -0.0392 0.4714 1.0000
3.500 0.7456 0.03139 0.01889 -0.0381 0.4670 1.0000
3.750 0.7666 0.03177 0.01921 -0.0371 0.4635 1.0000
4.000 0.7809 0.03275 0.02031 -0.0357 0.4583 1.0000
4.250 0.7950 0.03370 0.02138 -0.0342 0.4531 1.0000
4.500 0.8132 0.03429 0.02198 -0.0329 0.4492 1.0000
4.750 0.8344 0.03463 0.02229 -0.0318 0.4460 1.0000
5.000 0.8396 0.03626 0.02412 -0.0297 0.4400 1.0000
5.250 0.8509 0.03734 0.02530 -0.0279 0.4351 1.0000
5.500 0.8685 0.03791 0.02593 -0.0265 0.4315 1.0000
5.750 0.8876 0.03841 0.02642 -0.0251 0.4283 1.0000
6.000 0.8772 0.04097 0.02923 -0.0216 0.4213 1.0000
6.250 0.8869 0.04202 0.03035 -0.0196 0.4169 1.0000
6.500 0.9059 0.04244 0.03081 -0.0182 0.4138 1.0000
6.750 0.8871 0.04535 0.03389 -0.0139 0.4074 1.0000
7.000 0.8769 0.04752 0.03616 -0.0103 0.4015 1.0000
7.250 0.8923 0.04807 0.03675 -0.0085 0.3982 1.0000
7.750 0.8029 0.05616 0.04492 0.0034 0.3837 1.0000
8.000 0.8277 0.05598 0.04478 0.0047 0.3811 1.0000
8.500 0.7526 0.06526 0.05406 0.0107 0.3650 1.0000
9.000 0.7163 0.07249 0.06131 0.0137 0.3504 1.0000
9.250 0.7388 0.07240 0.06127 0.0153 0.3479 1.0000
9.500 0.6966 0.07857 0.06742 0.0158 0.3371 1.0000
9.750 0.7127 0.07920 0.06810 0.0171 0.3336 1.0000
10.250 0.6973 0.08534 0.07430 0.0184 0.3200 1.0000
10.500 0.7182 0.08554 0.07458 0.0197 0.3169 1.0000
10.750 0.6915 0.09089 0.07995 0.0193 0.3076 1.0000
11.000 0.7060 0.09181 0.08094 0.0202 0.3033 1.0000
11.500 0.6999 0.09779 0.08701 0.0203 0.2903 1.0000
11.750 0.7207 0.09807 0.08740 0.0214 0.2868 1.0000
12.000 0.7009 0.10316 0.09252 0.0203 0.2778 1.0000
12.250 0.7151 0.10427 0.09371 0.0209 0.2735 1.0000
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Polar data table (+)
Polar graphs
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