EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.9 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e434-il-1000000-n5.txt Download as CSV file: xf-e434-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 434 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0809 0.05818 0.05553 -0.0966 0.7355 0.0050
-7.500 -0.2071 0.03479 0.03147 -0.1118 0.7225 0.0034
-7.250 -0.2417 0.02202 0.01774 -0.1059 0.7190 0.0032
-7.000 -0.2293 0.01897 0.01424 -0.1040 0.7156 0.0031
-6.750 -0.2116 0.01686 0.01176 -0.1027 0.7123 0.0031
-6.500 -0.1902 0.01543 0.01005 -0.1018 0.7094 0.0031
-6.250 -0.1670 0.01432 0.00874 -0.1012 0.7066 0.0031
-6.000 -0.1428 0.01345 0.00771 -0.1007 0.7036 0.0031
-5.750 -0.1182 0.01269 0.00680 -0.1002 0.7003 0.0031
-5.500 -0.0933 0.01208 0.00606 -0.0998 0.6973 0.0031
-5.250 -0.0680 0.01153 0.00540 -0.0994 0.6944 0.0031
-5.000 -0.0420 0.01107 0.00488 -0.0992 0.6917 0.0032
-4.750 -0.0160 0.01062 0.00436 -0.0989 0.6886 0.0032
-4.500 0.0104 0.01028 0.00396 -0.0987 0.6855 0.0033
-4.250 0.0368 0.00997 0.00359 -0.0986 0.6825 0.0033
-4.000 0.0634 0.00971 0.00326 -0.0984 0.6795 0.0034
-3.750 0.0905 0.00943 0.00296 -0.0983 0.6768 0.0035
-3.500 0.1175 0.00915 0.00265 -0.0983 0.6737 0.0040
-3.250 0.1448 0.00899 0.00246 -0.0983 0.6704 0.0045
-3.000 0.1722 0.00884 0.00228 -0.0982 0.6671 0.0051
-2.750 0.1994 0.00870 0.00211 -0.0982 0.6640 0.0063
-2.500 0.2272 0.00856 0.00197 -0.0983 0.6611 0.0090
-2.250 0.2549 0.00841 0.00185 -0.0984 0.6576 0.0149
-2.000 0.2822 0.00825 0.00175 -0.0984 0.6541 0.0311
-1.750 0.3089 0.00802 0.00165 -0.0984 0.6506 0.0708
-1.500 0.3357 0.00774 0.00158 -0.0985 0.6473 0.1366
-1.250 0.3623 0.00740 0.00151 -0.0986 0.6435 0.2277
-1.000 0.3892 0.00714 0.00146 -0.0987 0.6395 0.3077
-0.750 0.4155 0.00684 0.00141 -0.0987 0.6354 0.4081
-0.500 0.4413 0.00633 0.00136 -0.0988 0.6316 0.5672
-0.250 0.4666 0.00588 0.00140 -0.0985 0.6270 0.7321
0.000 0.4938 0.00587 0.00144 -0.0984 0.6221 0.7729
0.250 0.5215 0.00591 0.00147 -0.0984 0.6175 0.7901
0.500 0.5494 0.00593 0.00151 -0.0985 0.6123 0.8043
0.750 0.5765 0.00599 0.00156 -0.0984 0.6066 0.8226
1.000 0.6035 0.00606 0.00164 -0.0982 0.6013 0.8395
1.250 0.6303 0.00612 0.00171 -0.0980 0.5952 0.8501
1.500 0.6577 0.00620 0.00175 -0.0980 0.5891 0.8542
1.750 0.6860 0.00625 0.00178 -0.0983 0.5827 0.8561
2.000 0.7132 0.00633 0.00182 -0.0982 0.5754 0.8578
2.250 0.7407 0.00639 0.00186 -0.0983 0.5683 0.8595
2.500 0.7674 0.00648 0.00192 -0.0982 0.5598 0.8615
2.750 0.7946 0.00656 0.00198 -0.0983 0.5511 0.8637
3.000 0.8212 0.00667 0.00206 -0.0982 0.5420 0.8658
3.250 0.8477 0.00679 0.00214 -0.0981 0.5310 0.8679
3.500 0.8742 0.00691 0.00222 -0.0981 0.5199 0.8699
3.750 0.9003 0.00705 0.00232 -0.0979 0.5084 0.8719
4.000 0.9253 0.00720 0.00244 -0.0976 0.4952 0.8739
4.250 0.9500 0.00737 0.00257 -0.0971 0.4811 0.8760
4.500 0.9741 0.00756 0.00272 -0.0966 0.4650 0.8785
4.750 0.9975 0.00779 0.00289 -0.0960 0.4467 0.8813
5.000 1.0203 0.00806 0.00308 -0.0953 0.4274 0.8840
5.250 1.0426 0.00835 0.00328 -0.0945 0.4077 0.8866
5.500 1.0642 0.00863 0.00350 -0.0936 0.3879 0.8892
5.750 1.0849 0.00892 0.00374 -0.0925 0.3685 0.8920
6.000 1.1043 0.00927 0.00400 -0.0911 0.3477 0.8953
6.250 1.1236 0.00961 0.00427 -0.0898 0.3270 0.8988
6.500 1.1415 0.01000 0.00457 -0.0883 0.3059 0.9024
6.750 1.1569 0.01036 0.00487 -0.0862 0.2859 0.9067
7.000 1.1713 0.01069 0.00516 -0.0838 0.2692 0.9119
7.500 1.1976 0.01146 0.00585 -0.0788 0.2360 0.9238
7.750 1.2096 0.01191 0.00624 -0.0763 0.2193 0.9317
8.000 1.2207 0.01232 0.00664 -0.0735 0.2049 0.9426
8.250 1.2319 0.01280 0.00710 -0.0709 0.1889 0.9623
8.750 1.2617 0.01404 0.00822 -0.0679 0.1559 1.0000
9.000 1.2742 0.01469 0.00882 -0.0660 0.1426 1.0000
9.250 1.2856 0.01542 0.00949 -0.0640 0.1290 1.0000
9.500 1.2964 0.01621 0.01024 -0.0620 0.1158 1.0000
9.750 1.3072 0.01704 0.01102 -0.0601 0.1039 1.0000
10.000 1.3170 0.01795 0.01188 -0.0582 0.0919 1.0000
10.250 1.3276 0.01886 0.01276 -0.0565 0.0822 1.0000
10.500 1.3397 0.01971 0.01362 -0.0550 0.0748 1.0000
10.750 1.3501 0.02070 0.01458 -0.0534 0.0672 1.0000
11.000 1.3589 0.02181 0.01567 -0.0518 0.0588 1.0000
11.250 1.3700 0.02281 0.01668 -0.0504 0.0530 1.0000
11.500 1.3795 0.02395 0.01780 -0.0489 0.0469 1.0000
11.750 1.3872 0.02524 0.01907 -0.0474 0.0400 1.0000
12.000 1.3953 0.02654 0.02037 -0.0460 0.0343 1.0000
12.250 1.4043 0.02779 0.02164 -0.0448 0.0301 1.0000
12.500 1.4120 0.02918 0.02304 -0.0435 0.0257 1.0000
13.000 1.4250 0.03226 0.02612 -0.0410 0.0180 1.0000
13.250 1.4333 0.03372 0.02762 -0.0400 0.0156 1.0000
13.500 1.4399 0.03536 0.02928 -0.0390 0.0132 1.0000
13.750 1.4460 0.03709 0.03104 -0.0381 0.0112 1.0000
14.000 1.4535 0.03873 0.03272 -0.0373 0.0097 1.0000
14.250 1.4589 0.04060 0.03462 -0.0365 0.0081 1.0000
14.500 1.4653 0.04245 0.03652 -0.0358 0.0070 1.0000
14.750 1.4709 0.04441 0.03853 -0.0352 0.0059 1.0000
15.000 1.4768 0.04638 0.04056 -0.0347 0.0053 1.0000
15.250 1.4811 0.04857 0.04280 -0.0342 0.0045 1.0000
15.500 1.4864 0.05071 0.04501 -0.0339 0.0039 1.0000
15.750 1.4902 0.05306 0.04742 -0.0336 0.0034 1.0000
16.000 1.4939 0.05548 0.04992 -0.0334 0.0030 1.0000
16.250 1.4973 0.05798 0.05248 -0.0334 0.0027 1.0000
16.500 1.4993 0.06071 0.05528 -0.0333 0.0023 1.0000
16.750 1.5010 0.06356 0.05821 -0.0335 0.0020 1.0000
17.000 1.5021 0.06654 0.06127 -0.0337 0.0017 1.0000
17.250 1.5029 0.06959 0.06441 -0.0341 0.0015 1.0000
17.500 1.5024 0.07289 0.06779 -0.0346 0.0014 1.0000
17.750 1.5018 0.07631 0.07130 -0.0352 0.0012 1.0000
18.000 1.5001 0.07994 0.07502 -0.0359 0.0010 1.0000
18.250 1.4986 0.08362 0.07880 -0.0368 0.0010 1.0000
18.500 1.4954 0.08761 0.08289 -0.0379 0.0008 1.0000
18.750 1.4916 0.09176 0.08714 -0.0392 0.0008 1.0000
19.000 1.4863 0.09625 0.09173 -0.0406 0.0007 1.0000
19.250 1.4813 0.10077 0.09635 -0.0422 0.0006 1.0000
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Polar data table (+)
Polar graphs
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