EPPLER 333 AIRFOIL (e333-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 333 AIRFOIL (e333-il) Reynolds number: 50,000 Max Cl/Cd: 17.44 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e333-il-50000.txt Download as CSV file: xf-e333-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 333 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3913 0.11512 0.10879 -0.0163 1.0000 0.1733
-9.000 -0.3595 0.10893 0.10257 -0.0134 1.0000 0.1835
-8.750 -0.3832 0.10814 0.10195 -0.0170 1.0000 0.1886
-8.500 -0.3561 0.10284 0.09666 -0.0146 1.0000 0.2000
-8.250 -0.3610 0.09990 0.09384 -0.0157 1.0000 0.2073
-8.000 -0.3715 0.09781 0.09189 -0.0167 1.0000 0.2189
-7.750 -0.3568 0.09387 0.08801 -0.0152 1.0000 0.2322
-7.500 -0.3520 0.09064 0.08488 -0.0144 1.0000 0.2457
-7.250 -0.3516 0.08780 0.08216 -0.0136 1.0000 0.2607
-7.000 -0.3566 0.08521 0.07972 -0.0126 1.0000 0.2776
-6.750 -0.3675 0.08301 0.07769 -0.0110 1.0000 0.2946
-6.500 -0.3574 0.08009 0.07487 -0.0078 1.0000 0.3236
-6.250 -0.3636 0.07810 0.07307 -0.0041 1.0000 0.3564
-6.000 -0.3206 0.07478 0.06974 0.0020 1.0000 0.4297
-5.750 -0.2666 0.07154 0.06647 0.0085 1.0000 0.5361
-5.500 -0.1659 0.06663 0.06139 0.0122 1.0000 0.7243
-4.750 -0.0965 0.05696 0.05205 0.0083 1.0000 0.8061
-4.500 -0.1631 0.05824 0.05377 0.0163 1.0000 0.7474
-4.250 -0.2067 0.06036 0.05616 0.0248 1.0000 0.7584
-4.000 -0.2609 0.05945 0.05541 0.0220 0.9772 0.6830
-3.750 -0.3138 0.05612 0.05216 0.0151 0.9430 0.6193
-3.500 -0.2448 0.04601 0.03875 -0.0344 0.9116 0.1889
-3.250 -0.1885 0.04173 0.03372 -0.0379 0.8993 0.1395
-3.000 -0.1323 0.03828 0.02956 -0.0414 0.8880 0.1202
-2.750 -0.0891 0.03629 0.02688 -0.0427 0.8738 0.1135
-2.500 -0.0476 0.03421 0.02450 -0.0443 0.8597 0.1155
-2.250 -0.0047 0.03246 0.02244 -0.0457 0.8460 0.1176
-2.000 0.2739 0.02276 0.01492 -0.0803 0.8443 1.0000
-1.750 0.2990 0.02300 0.01468 -0.0795 0.8269 1.0000
-1.500 0.3197 0.02342 0.01477 -0.0784 0.8095 1.0000
-1.250 0.3415 0.02383 0.01488 -0.0774 0.7941 1.0000
-1.000 0.3631 0.02426 0.01504 -0.0764 0.7799 1.0000
-0.750 0.3840 0.02472 0.01524 -0.0752 0.7664 1.0000
-0.500 0.4026 0.02532 0.01567 -0.0739 0.7530 1.0000
-0.250 0.4207 0.02601 0.01619 -0.0727 0.7406 1.0000
0.000 0.4392 0.02670 0.01672 -0.0714 0.7290 1.0000
0.250 0.4605 0.02720 0.01703 -0.0701 0.7194 1.0000
0.500 0.4766 0.02809 0.01784 -0.0689 0.7081 1.0000
0.750 0.4924 0.02903 0.01869 -0.0676 0.6979 1.0000
1.000 0.5147 0.02951 0.01901 -0.0663 0.6896 1.0000
1.250 0.5258 0.03082 0.02030 -0.0649 0.6790 1.0000
1.500 0.5416 0.03182 0.02123 -0.0635 0.6705 1.0000
1.750 0.5576 0.03279 0.02214 -0.0620 0.6616 1.0000
2.000 0.5666 0.03429 0.02362 -0.0604 0.6531 1.0000
2.250 0.5849 0.03515 0.02441 -0.0590 0.6455 1.0000
2.500 0.5867 0.03709 0.02637 -0.0568 0.6369 1.0000
2.750 0.6054 0.03797 0.02719 -0.0555 0.6300 1.0000
3.000 0.5984 0.04042 0.02966 -0.0527 0.6218 1.0000
3.250 0.6154 0.04143 0.03065 -0.0512 0.6150 1.0000
3.500 0.6008 0.04428 0.03350 -0.0479 0.6080 1.0000
3.750 0.6025 0.04617 0.03538 -0.0456 0.6013 1.0000
4.000 0.6028 0.04821 0.03740 -0.0432 0.5953 1.0000
4.250 0.5680 0.05179 0.04094 -0.0386 0.5905 1.0000
4.500 0.5967 0.05266 0.04181 -0.0384 0.5838 1.0000
4.750 0.5661 0.05594 0.04502 -0.0339 0.5806 1.0000
5.000 0.5401 0.05909 0.04812 -0.0305 0.5786 1.0000
5.250 0.5286 0.06190 0.05091 -0.0286 0.5773 1.0000
5.500 0.5222 0.06463 0.05362 -0.0273 0.5765 1.0000
5.750 0.5200 0.06748 0.05646 -0.0267 0.5787 1.0000
6.000 0.5240 0.07050 0.05951 -0.0269 0.5839 1.0000
6.250 0.4216 0.07792 0.06699 -0.0280 0.7067 1.0000
6.500 0.4282 0.07955 0.06861 -0.0269 0.6940 1.0000
6.750 0.4401 0.08160 0.07066 -0.0265 0.6804 1.0000
7.000 0.4530 0.08382 0.07288 -0.0263 0.6680 1.0000
7.250 0.4780 0.08697 0.07606 -0.0274 0.6578 1.0000
7.500 0.4981 0.08957 0.07871 -0.0278 0.6439 1.0000
7.750 0.5013 0.09107 0.08023 -0.0266 0.6302 1.0000
8.000 0.5047 0.09291 0.08208 -0.0256 0.6179 1.0000
8.250 0.5138 0.09525 0.08444 -0.0253 0.6062 1.0000
8.500 0.5300 0.09808 0.08732 -0.0256 0.5949 1.0000
8.750 0.5561 0.10149 0.09084 -0.0265 0.5831 1.0000
9.000 0.5551 0.10302 0.09238 -0.0254 0.5699 1.0000
9.250 0.5582 0.10513 0.09453 -0.0248 0.5578 1.0000
9.500 0.5679 0.10793 0.09738 -0.0249 0.5478 1.0000
9.750 0.5985 0.11215 0.10169 -0.0261 0.5370 1.0000
10.000 0.5980 0.11375 0.10334 -0.0253 0.5237 1.0000
10.250 0.5954 0.11575 0.10538 -0.0248 0.5125 1.0000
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Polar data table (+)
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