EPPLER 635 AIRFOIL (e635-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 635 AIRFOIL (e635-il) Reynolds number: 50,000 Max Cl/Cd: 14.58 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e635-il-50000.txt Download as CSV file: xf-e635-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 635 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4624 0.10364 0.09784 0.0166 1.0000 0.2614
-8.500 -0.4585 0.10033 0.09460 0.0168 1.0000 0.2783
-8.250 -0.4607 0.09750 0.09187 0.0168 1.0000 0.2971
-8.000 -0.4464 0.09385 0.08829 0.0185 1.0000 0.3231
-7.750 -0.4378 0.09077 0.08528 0.0204 1.0000 0.3546
-7.500 -0.4302 0.08794 0.08255 0.0223 1.0000 0.3872
-7.250 -0.4103 0.08456 0.07922 0.0251 1.0000 0.4285
-7.000 -0.3912 0.08168 0.07639 0.0282 1.0000 0.4771
-6.750 -0.3611 0.07844 0.07318 0.0314 1.0000 0.5366
-6.500 -0.3314 0.07597 0.07076 0.0356 1.0000 0.6176
-5.500 -0.3423 0.06219 0.05758 0.0304 1.0000 0.5778
-5.250 -0.4182 0.05845 0.05426 0.0265 1.0000 0.5087
-5.000 -0.4627 0.05748 0.05360 0.0297 1.0000 0.5000
-4.750 -0.4692 0.04848 0.04192 0.0010 0.9678 0.1933
-4.500 -0.4107 0.04265 0.03516 -0.0040 0.9478 0.1456
-4.250 -0.3555 0.03855 0.03028 -0.0085 0.9288 0.1354
-4.000 -0.3046 0.03574 0.02678 -0.0115 0.9085 0.1310
-3.750 -0.2587 0.03311 0.02371 -0.0137 0.8874 0.1289
-3.500 -0.2156 0.03126 0.02136 -0.0150 0.8673 0.1312
-3.250 -0.1766 0.02955 0.01951 -0.0161 0.8464 0.1385
-3.000 0.0970 0.02256 0.01507 -0.0476 0.8206 1.0000
-2.750 0.1162 0.02281 0.01490 -0.0463 0.7991 1.0000
-2.500 0.1350 0.02307 0.01480 -0.0449 0.7804 1.0000
-2.250 0.1545 0.02336 0.01476 -0.0436 0.7638 1.0000
-2.000 0.1748 0.02367 0.01480 -0.0426 0.7483 1.0000
-1.750 0.1951 0.02401 0.01490 -0.0416 0.7338 1.0000
-1.500 0.2161 0.02440 0.01506 -0.0409 0.7200 1.0000
-1.250 0.2377 0.02484 0.01530 -0.0403 0.7071 1.0000
-1.000 0.2592 0.02530 0.01559 -0.0396 0.6951 1.0000
-0.750 0.2797 0.02576 0.01586 -0.0386 0.6844 1.0000
-0.500 0.3013 0.02628 0.01623 -0.0380 0.6735 1.0000
-0.250 0.3236 0.02693 0.01679 -0.0379 0.6626 1.0000
0.000 0.3445 0.02752 0.01724 -0.0370 0.6533 1.0000
0.250 0.3660 0.02819 0.01781 -0.0366 0.6438 1.0000
0.500 0.3877 0.02905 0.01862 -0.0366 0.6343 1.0000
0.750 0.4076 0.02963 0.01907 -0.0352 0.6267 1.0000
1.000 0.4290 0.03078 0.02024 -0.0358 0.6171 1.0000
1.250 0.4488 0.03147 0.02082 -0.0345 0.6102 1.0000
1.500 0.4686 0.03282 0.02221 -0.0351 0.6010 1.0000
1.750 0.4879 0.03369 0.02300 -0.0339 0.5944 1.0000
2.000 0.5053 0.03532 0.02470 -0.0345 0.5862 1.0000
2.250 0.5249 0.03600 0.02529 -0.0328 0.5806 1.0000
2.500 0.5376 0.03831 0.02771 -0.0339 0.5721 1.0000
2.750 0.5563 0.03920 0.02855 -0.0324 0.5664 1.0000
3.000 0.5633 0.04197 0.03141 -0.0332 0.5597 1.0000
3.250 0.5762 0.04362 0.03307 -0.0323 0.5537 1.0000
3.500 0.5873 0.04550 0.03498 -0.0315 0.5484 1.0000
3.750 0.5801 0.04911 0.03864 -0.0315 0.5441 1.0000
4.000 0.5805 0.05171 0.04125 -0.0306 0.5400 1.0000
4.250 0.6022 0.05274 0.04226 -0.0291 0.5348 1.0000
4.500 0.5838 0.05674 0.04627 -0.0283 0.5337 1.0000
4.750 0.5734 0.06009 0.04960 -0.0271 0.5342 1.0000
5.000 0.5655 0.06317 0.05267 -0.0258 0.5355 1.0000
5.250 0.3651 0.07226 0.06158 -0.0219 0.7072 1.0000
5.500 0.3767 0.07422 0.06352 -0.0211 0.6949 1.0000
5.750 0.3921 0.07642 0.06571 -0.0208 0.6828 1.0000
6.000 0.4115 0.07890 0.06821 -0.0209 0.6699 1.0000
6.250 0.4332 0.08152 0.07085 -0.0212 0.6566 1.0000
6.500 0.4356 0.08283 0.07214 -0.0194 0.6431 1.0000
6.750 0.4420 0.08458 0.07389 -0.0181 0.6296 1.0000
7.000 0.4489 0.08648 0.07579 -0.0170 0.6170 1.0000
7.250 0.4595 0.08878 0.07810 -0.0165 0.6061 1.0000
7.500 0.4901 0.09254 0.08194 -0.0176 0.5957 1.0000
7.750 0.4922 0.09392 0.08334 -0.0161 0.5820 1.0000
8.000 0.4929 0.09553 0.08495 -0.0148 0.5693 1.0000
8.250 0.4974 0.09770 0.08715 -0.0139 0.5586 1.0000
8.500 0.5172 0.10099 0.09049 -0.0142 0.5489 1.0000
8.750 0.5341 0.10377 0.09336 -0.0140 0.5359 1.0000
9.000 0.5281 0.10506 0.09466 -0.0126 0.5240 1.0000
9.250 0.5318 0.10747 0.09710 -0.0121 0.5141 1.0000
9.500 0.5516 0.11101 0.10071 -0.0123 0.5038 1.0000
9.750 0.5635 0.11361 0.10338 -0.0119 0.4911 1.0000
10.000 0.5555 0.11515 0.10493 -0.0110 0.4809 1.0000
10.250 0.5654 0.11825 0.10809 -0.0109 0.4717 1.0000
10.500 0.5944 0.12278 0.11277 -0.0114 0.4601 1.0000
10.750 0.4516 0.11973 0.11034 0.0000 0.4427 1.0000
11.000 0.4588 0.12223 0.11291 0.0003 0.4323 1.0000
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Polar data table (+)
Polar graphs
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