EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 50,000 Max Cl/Cd: 26.71 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e426-il-50000-n5.txt Download as CSV file: xf-e426-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 426 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6398 0.11347 0.10562 0.0040 1.0000 0.0907
-11.250 -0.6497 0.10707 0.09928 0.0005 1.0000 0.0936
-11.000 -0.6760 0.09727 0.08957 -0.0058 1.0000 0.0959
-10.750 -0.6618 0.09635 0.08864 -0.0048 1.0000 0.1000
-10.500 -0.6690 0.09085 0.08318 -0.0076 1.0000 0.1036
-10.250 -0.7075 0.07862 0.07104 -0.0165 1.0000 0.1059
-10.000 -0.7647 0.06584 0.05828 -0.0263 1.0000 0.1053
-9.750 -0.8058 0.05785 0.05008 -0.0296 1.0000 0.1062
-9.500 -0.8244 0.05217 0.04403 -0.0307 1.0000 0.1098
-9.250 -0.8035 0.05199 0.04388 -0.0296 1.0000 0.1158
-9.000 -0.8149 0.04659 0.03780 -0.0302 1.0000 0.1218
-8.750 -0.7896 0.04680 0.03819 -0.0291 1.0000 0.1277
-8.500 -0.7849 0.04345 0.03428 -0.0289 1.0000 0.1350
-8.250 -0.7635 0.04276 0.03365 -0.0281 1.0000 0.1410
-8.000 -0.7492 0.04076 0.03126 -0.0276 1.0000 0.1486
-7.750 -0.7305 0.03929 0.02967 -0.0270 1.0000 0.1547
-7.500 -0.7108 0.03791 0.02811 -0.0264 1.0000 0.1610
-7.250 -0.6940 0.03569 0.02535 -0.0260 1.0000 0.1670
-7.000 -0.6713 0.03441 0.02407 -0.0254 1.0000 0.1709
-6.750 -0.6494 0.03307 0.02257 -0.0248 1.0000 0.1760
-6.500 -0.6281 0.03153 0.02063 -0.0243 1.0000 0.1819
-6.250 -0.6049 0.03029 0.01934 -0.0237 1.0000 0.1862
-6.000 -0.5814 0.02916 0.01811 -0.0231 1.0000 0.1908
-5.750 -0.5581 0.02802 0.01674 -0.0225 1.0000 0.1969
-5.500 -0.5345 0.02704 0.01571 -0.0218 1.0000 0.2029
-5.250 -0.5109 0.02616 0.01478 -0.0211 1.0000 0.2098
-5.000 -0.4868 0.02525 0.01370 -0.0205 1.0000 0.2169
-4.750 -0.4632 0.02444 0.01296 -0.0197 1.0000 0.2233
-4.500 -0.4393 0.02371 0.01208 -0.0190 1.0000 0.2323
-4.250 -0.4162 0.02301 0.01152 -0.0181 1.0000 0.2412
-4.000 -0.3928 0.02237 0.01086 -0.0173 1.0000 0.2517
-3.750 -0.3697 0.02178 0.01030 -0.0165 1.0000 0.2635
-3.500 -0.3469 0.02120 0.00983 -0.0156 1.0000 0.2762
-3.250 -0.3239 0.02066 0.00939 -0.0149 1.0000 0.2915
-3.000 -0.3019 0.02016 0.00901 -0.0140 1.0000 0.3095
-2.750 -0.2804 0.01968 0.00867 -0.0130 1.0000 0.3304
-2.500 -0.2598 0.01922 0.00845 -0.0119 1.0000 0.3557
-2.250 -0.2400 0.01880 0.00827 -0.0108 1.0000 0.3886
-2.000 -0.2212 0.01846 0.00819 -0.0094 1.0000 0.4313
-1.750 -0.2038 0.01819 0.00821 -0.0078 1.0000 0.4829
-1.500 -0.1824 0.01801 0.00834 -0.0069 0.9959 0.5403
-1.250 -0.1416 0.01791 0.00852 -0.0093 0.9757 0.6083
-1.000 -0.1011 0.01784 0.00867 -0.0112 0.9556 0.6699
-0.750 -0.0619 0.01775 0.00876 -0.0126 0.9344 0.7237
-0.500 -0.0156 0.01761 0.00877 -0.0147 0.9114 0.7768
-0.250 0.0313 0.01743 0.00867 -0.0165 0.8807 0.8263
0.000 0.0796 0.01728 0.00853 -0.0183 0.8454 0.8764
0.250 0.1387 0.01718 0.00839 -0.0223 0.8091 0.9350
0.500 0.2038 0.01705 0.00812 -0.0283 0.7695 0.9850
0.750 0.2364 0.01704 0.00791 -0.0291 0.7338 1.0000
1.000 0.2547 0.01713 0.00781 -0.0272 0.7015 1.0000
1.250 0.2738 0.01726 0.00775 -0.0254 0.6689 1.0000
1.500 0.2937 0.01743 0.00773 -0.0237 0.6354 1.0000
1.750 0.3145 0.01764 0.00774 -0.0220 0.6011 1.0000
2.000 0.3358 0.01788 0.00778 -0.0205 0.5653 1.0000
2.250 0.3575 0.01816 0.00786 -0.0190 0.5286 1.0000
2.500 0.3797 0.01850 0.00797 -0.0177 0.4923 1.0000
2.750 0.4021 0.01889 0.00814 -0.0165 0.4573 1.0000
3.000 0.4251 0.01933 0.00839 -0.0154 0.4251 1.0000
3.250 0.4492 0.01982 0.00870 -0.0147 0.3970 1.0000
3.500 0.4737 0.02036 0.00905 -0.0140 0.3748 1.0000
3.750 0.4987 0.02091 0.00947 -0.0135 0.3553 1.0000
4.000 0.5238 0.02148 0.00993 -0.0129 0.3381 1.0000
4.250 0.5489 0.02207 0.01042 -0.0124 0.3236 1.0000
4.500 0.5740 0.02269 0.01099 -0.0119 0.3099 1.0000
4.750 0.5990 0.02332 0.01161 -0.0114 0.2969 1.0000
5.000 0.6242 0.02401 0.01227 -0.0109 0.2858 1.0000
5.250 0.6491 0.02471 0.01287 -0.0103 0.2756 1.0000
5.500 0.6740 0.02546 0.01374 -0.0099 0.2651 1.0000
5.750 0.6988 0.02626 0.01452 -0.0093 0.2561 1.0000
6.000 0.7234 0.02708 0.01542 -0.0088 0.2469 1.0000
6.250 0.7478 0.02800 0.01641 -0.0083 0.2387 1.0000
6.500 0.7718 0.02890 0.01736 -0.0078 0.2301 1.0000
6.750 0.7954 0.02993 0.01852 -0.0073 0.2222 1.0000
7.000 0.8188 0.03096 0.01967 -0.0067 0.2144 1.0000
7.250 0.8418 0.03206 0.02085 -0.0061 0.2073 1.0000
7.500 0.8634 0.03326 0.02226 -0.0055 0.1993 1.0000
7.750 0.8872 0.03428 0.02323 -0.0049 0.1935 1.0000
8.000 0.9054 0.03589 0.02527 -0.0042 0.1856 1.0000
8.250 0.9276 0.03691 0.02630 -0.0036 0.1794 1.0000
8.500 0.9449 0.03868 0.02839 -0.0028 0.1730 1.0000
8.750 0.9627 0.04017 0.03010 -0.0020 0.1664 1.0000
9.000 0.9846 0.04119 0.03106 -0.0014 0.1614 1.0000
9.250 0.9930 0.04383 0.03423 -0.0004 0.1550 1.0000
9.500 1.0102 0.04516 0.03566 0.0004 0.1496 1.0000
9.750 1.0238 0.04703 0.03771 0.0013 0.1450 1.0000
10.000 1.0234 0.05037 0.04150 0.0022 0.1401 1.0000
10.250 1.0347 0.05207 0.04333 0.0031 0.1356 1.0000
10.500 1.0472 0.05375 0.04507 0.0039 0.1320 1.0000
10.750 1.0203 0.05927 0.05104 0.0045 0.1294 1.0000
11.000 0.9791 0.06568 0.05770 0.0041 0.1282 1.0000
11.250 0.8814 0.08324 0.07534 -0.0078 0.1287 1.0000
11.500 0.8244 0.09952 0.09155 -0.0189 0.1257 1.0000
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Polar data table (+)
Polar graphs
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