E71 (5.15%) (e71-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.05 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e71-il-1000000-n5.txt Download as CSV file: xf-e71-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3139 0.10048 0.09878 -0.0416 0.9917 0.0041
-8.500 -0.3025 0.09767 0.09598 -0.0437 0.9904 0.0049
-8.250 -0.2993 0.09030 0.08862 -0.0481 0.9883 0.0033
-8.000 -0.2883 0.08630 0.08463 -0.0514 0.9866 0.0033
-7.750 -0.2756 0.08258 0.08091 -0.0551 0.9851 0.0033
-7.500 -0.2591 0.08017 0.07851 -0.0583 0.9839 0.0035
-7.250 -0.2426 0.07626 0.07461 -0.0632 0.9826 0.0036
-7.000 -0.2360 0.07330 0.07166 -0.0646 0.9774 0.0036
-6.750 -0.2173 0.07014 0.06850 -0.0691 0.9746 0.0039
-6.500 -0.1937 0.06589 0.06424 -0.0759 0.9726 0.0042
-6.250 -0.1649 0.06115 0.05949 -0.0843 0.9711 0.0048
-5.000 0.0505 0.02297 0.02050 -0.1458 0.9589 0.0078
-4.750 0.0854 0.02146 0.01885 -0.1490 0.9583 0.0084
-4.500 0.1243 0.01869 0.01581 -0.1531 0.9577 0.0092
-4.250 0.1565 0.01618 0.01299 -0.1551 0.9548 0.0097
-4.000 0.1881 0.01409 0.01060 -0.1566 0.9514 0.0099
-3.750 0.2216 0.01272 0.00899 -0.1582 0.9494 0.0106
-3.500 0.2574 0.01096 0.00693 -0.1602 0.9481 0.0100
-3.250 0.2925 0.00968 0.00542 -0.1619 0.9467 0.0096
-3.000 0.3279 0.00866 0.00424 -0.1636 0.9454 0.0093
-2.750 0.3584 0.00794 0.00340 -0.1642 0.9414 0.0091
-2.500 0.3905 0.00735 0.00272 -0.1651 0.9366 0.0089
-2.250 0.4273 0.00683 0.00210 -0.1671 0.9327 0.0089
-2.000 0.4614 0.00645 0.00164 -0.1684 0.9256 0.0090
-1.750 0.4984 0.00612 0.00123 -0.1703 0.9185 0.0096
-1.500 0.5320 0.00593 0.00097 -0.1715 0.9072 0.0117
-1.000 0.5934 0.00583 0.00073 -0.1726 0.8741 0.0133
-0.750 0.6214 0.00584 0.00064 -0.1726 0.8549 0.0139
-0.500 0.6485 0.00589 0.00057 -0.1723 0.8337 0.0157
-0.250 0.6745 0.00598 0.00054 -0.1717 0.8082 0.0175
0.000 0.7003 0.00605 0.00057 -0.1712 0.7804 0.0451
0.250 0.7273 0.00592 0.00065 -0.1712 0.7525 0.1804
0.500 0.7535 0.00590 0.00076 -0.1710 0.7219 0.2882
0.750 0.7790 0.00595 0.00090 -0.1707 0.6841 0.3920
1.000 0.8053 0.00587 0.00115 -0.1707 0.6362 0.6253
1.250 0.8301 0.00597 0.00136 -0.1702 0.5868 0.7638
1.500 0.8520 0.00614 0.00155 -0.1689 0.5357 0.8653
1.750 0.8693 0.00631 0.00165 -0.1665 0.4859 1.0000
2.000 0.8932 0.00678 0.00187 -0.1658 0.4248 1.0000
2.250 0.9162 0.00738 0.00212 -0.1650 0.3484 1.0000
2.500 0.9357 0.00848 0.00253 -0.1637 0.2095 1.0000
2.750 0.9580 0.00925 0.00288 -0.1628 0.1247 1.0000
3.000 0.9818 0.00983 0.00319 -0.1622 0.0718 1.0000
3.250 1.0056 0.01044 0.00354 -0.1615 0.0251 1.0000
3.500 1.0306 0.01087 0.00385 -0.1609 0.0068 1.0000
3.750 1.0567 0.01111 0.00413 -0.1605 0.0051 1.0000
4.000 1.0826 0.01139 0.00446 -0.1601 0.0041 1.0000
4.250 1.1081 0.01174 0.00489 -0.1596 0.0033 1.0000
4.500 1.1335 0.01210 0.00529 -0.1590 0.0032 1.0000
4.750 1.1583 0.01253 0.00579 -0.1584 0.0031 1.0000
5.000 1.1827 0.01305 0.00639 -0.1577 0.0030 1.0000
5.250 1.2069 0.01359 0.00699 -0.1569 0.0028 1.0000
5.500 1.2308 0.01416 0.00768 -0.1561 0.0026 1.0000
5.750 1.2546 0.01470 0.00828 -0.1553 0.0024 1.0000
6.000 1.2778 0.01538 0.00903 -0.1544 0.0022 1.0000
6.250 1.3004 0.01612 0.00986 -0.1534 0.0021 1.0000
6.500 1.3227 0.01691 0.01073 -0.1524 0.0019 1.0000
6.750 1.3450 0.01768 0.01158 -0.1514 0.0018 1.0000
7.000 1.3670 0.01850 0.01248 -0.1504 0.0017 1.0000
7.250 1.3885 0.01938 0.01344 -0.1493 0.0016 1.0000
7.500 1.4078 0.02072 0.01490 -0.1479 0.0014 1.0000
7.750 1.4223 0.02343 0.01792 -0.1455 0.0012 1.0000
8.000 1.4427 0.02459 0.01924 -0.1442 0.0012 1.0000
8.250 1.4621 0.02598 0.02080 -0.1428 0.0011 1.0000
8.500 1.4794 0.02782 0.02286 -0.1410 0.0011 1.0000
8.750 1.4941 0.03018 0.02550 -0.1388 0.0010 1.0000
9.000 1.5058 0.03293 0.02857 -0.1363 0.0010 1.0000
9.250 1.5131 0.03630 0.03230 -0.1332 0.0010 1.0000
9.500 1.5158 0.03996 0.03632 -0.1296 0.0010 1.0000
9.750 1.5129 0.04394 0.04065 -0.1255 0.0010 1.0000
10.000 1.5015 0.04799 0.04503 -0.1204 0.0010 1.0000
10.250 1.4835 0.05156 0.04884 -0.1146 0.0010 1.0000
10.500 1.4661 0.05531 0.05283 -0.1100 0.0010 1.0000
10.750 1.4456 0.05982 0.05756 -0.1064 0.0010 1.0000
11.000 1.4247 0.06477 0.06272 -0.1041 0.0010 1.0000
11.250 1.4042 0.07024 0.06836 -0.1034 0.0010 1.0000
11.500 1.3816 0.07682 0.07512 -0.1045 0.0010 1.0000
11.750 1.3577 0.08481 0.08329 -0.1078 0.0010 1.0000
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Polar data table (+)
Polar graphs
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