E471 (6.25%) (e471-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 1,000,000 Max Cl/Cd: 189.49 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e471-il-1000000.txt Download as CSV file: xf-e471-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2813 0.09297 0.09136 -0.0502 0.9902 0.0069
-8.000 -0.2669 0.08885 0.08724 -0.0543 0.9881 0.0070
-7.750 -0.2576 0.08388 0.08228 -0.0578 0.9864 0.0075
-7.500 -0.2397 0.08063 0.07903 -0.0618 0.9850 0.0077
-7.250 -0.2199 0.07742 0.07581 -0.0665 0.9836 0.0083
-7.000 -0.2092 0.07439 0.07279 -0.0691 0.9780 0.0087
-6.750 -0.1863 0.07004 0.06844 -0.0757 0.9747 0.0093
-6.500 -0.1529 0.06540 0.06378 -0.0854 0.9727 0.0108
-6.250 -0.1195 0.06063 0.05900 -0.0946 0.9714 0.0110
-6.000 -0.0902 0.05573 0.05408 -0.1030 0.9677 0.0111
-5.750 -0.0588 0.05039 0.04868 -0.1119 0.9630 0.0111
-5.500 -0.0151 0.04354 0.04175 -0.1243 0.9611 0.0112
-5.250 0.0356 0.03493 0.03295 -0.1377 0.9598 0.0112
-5.000 0.0874 0.02228 0.01966 -0.1532 0.9580 0.0126
-4.750 0.1145 0.02073 0.01797 -0.1545 0.9537 0.0133
-4.500 0.1460 0.01863 0.01565 -0.1565 0.9502 0.0145
-4.250 0.1792 0.01741 0.01425 -0.1580 0.9477 0.0171
-4.000 0.2123 0.01724 0.01393 -0.1588 0.9456 0.0182
-3.750 0.2448 0.01521 0.01158 -0.1604 0.9419 0.0183
-3.250 0.3109 0.00964 0.00529 -0.1635 0.9337 0.0173
-3.000 0.3429 0.00867 0.00418 -0.1644 0.9300 0.0172
-2.750 0.3713 0.00805 0.00349 -0.1645 0.9239 0.0173
-2.500 0.4026 0.00744 0.00278 -0.1653 0.9193 0.0173
-2.250 0.4321 0.00693 0.00217 -0.1656 0.9128 0.0169
-2.000 0.4623 0.00657 0.00171 -0.1660 0.9062 0.0169
-1.750 0.4910 0.00634 0.00140 -0.1661 0.8986 0.0173
-1.500 0.5204 0.00619 0.00115 -0.1663 0.8912 0.0183
-1.250 0.5482 0.00607 0.00095 -0.1661 0.8825 0.0212
-1.000 0.5764 0.00601 0.00086 -0.1661 0.8746 0.0267
-0.750 0.6053 0.00566 0.00082 -0.1665 0.8659 0.1471
-0.500 0.6338 0.00536 0.00085 -0.1669 0.8569 0.2851
-0.250 0.6621 0.00518 0.00088 -0.1672 0.8483 0.3906
0.000 0.6901 0.00498 0.00093 -0.1673 0.8388 0.5077
0.250 0.7181 0.00466 0.00105 -0.1675 0.8289 0.6964
0.500 0.7350 0.00415 0.00111 -0.1647 0.8185 1.0000
0.750 0.7624 0.00423 0.00113 -0.1646 0.8079 1.0000
1.000 0.7896 0.00431 0.00115 -0.1644 0.7966 1.0000
1.250 0.8167 0.00440 0.00118 -0.1642 0.7843 1.0000
1.500 0.8435 0.00449 0.00122 -0.1639 0.7704 1.0000
1.750 0.8700 0.00461 0.00129 -0.1635 0.7548 1.0000
2.000 0.8963 0.00473 0.00135 -0.1632 0.7368 1.0000
2.250 0.9220 0.00489 0.00143 -0.1627 0.7151 1.0000
2.500 0.9473 0.00508 0.00152 -0.1621 0.6889 1.0000
2.750 0.9719 0.00532 0.00164 -0.1614 0.6582 1.0000
3.000 0.9950 0.00567 0.00182 -0.1604 0.6106 1.0000
3.250 1.0146 0.00632 0.00208 -0.1588 0.5268 1.0000
3.500 1.0331 0.00718 0.00245 -0.1572 0.4256 1.0000
3.750 1.0538 0.00791 0.00280 -0.1560 0.3456 1.0000
4.000 1.0744 0.00867 0.00318 -0.1548 0.2681 1.0000
4.250 1.0944 0.00952 0.00363 -0.1536 0.1880 1.0000
4.500 1.1156 0.01026 0.00405 -0.1525 0.1260 1.0000
4.750 1.1367 0.01101 0.00450 -0.1514 0.0731 1.0000
5.000 1.1555 0.01210 0.00520 -0.1499 0.0125 1.0000
5.250 1.1790 0.01262 0.00572 -0.1490 0.0070 1.0000
5.500 1.2028 0.01310 0.00628 -0.1482 0.0062 1.0000
5.750 1.2256 0.01373 0.00704 -0.1471 0.0058 1.0000
6.000 1.2482 0.01434 0.00773 -0.1461 0.0054 1.0000
6.250 1.2709 0.01492 0.00837 -0.1452 0.0053 1.0000
6.500 1.2927 0.01563 0.00916 -0.1440 0.0051 1.0000
6.750 1.3138 0.01639 0.01001 -0.1428 0.0049 1.0000
7.000 1.3342 0.01724 0.01095 -0.1414 0.0047 1.0000
7.250 1.3541 0.01814 0.01196 -0.1400 0.0045 1.0000
7.500 1.3735 0.01913 0.01302 -0.1385 0.0041 1.0000
7.750 1.3920 0.02024 0.01423 -0.1369 0.0039 1.0000
8.000 1.4093 0.02161 0.01570 -0.1352 0.0037 1.0000
8.250 1.4260 0.02330 0.01754 -0.1332 0.0036 1.0000
8.500 1.4416 0.02682 0.02144 -0.1306 0.0041 1.0000
8.750 1.4556 0.03532 0.03075 -0.1265 0.0072 1.0000
9.000 1.4677 0.03754 0.03317 -0.1243 0.0068 1.0000
9.250 1.4779 0.03979 0.03560 -0.1219 0.0066 1.0000
9.500 1.4858 0.04218 0.03818 -0.1194 0.0064 1.0000
9.750 1.4887 0.04496 0.04117 -0.1163 0.0062 1.0000
10.000 1.4857 0.04823 0.04466 -0.1127 0.0060 1.0000
10.250 1.4692 0.05219 0.04886 -0.1073 0.0059 1.0000
10.500 1.4449 0.05645 0.05336 -0.1016 0.0058 1.0000
10.750 1.4131 0.06194 0.05913 -0.0965 0.0057 1.0000
11.000 1.3577 0.07121 0.06874 -0.0924 0.0056 1.0000
11.250 1.3379 0.07608 0.07379 -0.0914 0.0056 1.0000
11.500 1.3170 0.08164 0.07951 -0.0916 0.0056 1.0000
11.750 1.2969 0.08774 0.08576 -0.0931 0.0056 1.0000
12.000 1.2156 0.08781 0.08601 -0.0855 0.0062 1.0000
12.250 1.1727 0.09651 0.09493 -0.0888 0.0063 1.0000
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Polar data table (+)
Polar graphs
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