E71 (5.15%) (e71-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 1,000,000 Max Cl/Cd: 204.95 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e71-il-1000000.txt Download as CSV file: xf-e71-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3257 0.09133 0.08977 -0.0343 0.9925 0.0064
-7.250 -0.3129 0.08802 0.08646 -0.0375 0.9897 0.0067
-7.000 -0.2983 0.08456 0.08301 -0.0413 0.9871 0.0072
-6.750 -0.2791 0.08071 0.07915 -0.0466 0.9849 0.0073
-6.500 -0.2460 0.07588 0.07431 -0.0559 0.9835 0.0086
-6.250 -0.2288 0.07218 0.07062 -0.0605 0.9780 0.0088
-6.000 -0.2020 0.06760 0.06602 -0.0678 0.9752 0.0089
-5.000 -0.0397 0.03900 0.03715 -0.1171 0.9659 0.0096
-4.750 0.0017 0.03404 0.03205 -0.1254 0.9640 0.0101
-4.500 0.0448 0.02957 0.02741 -0.1327 0.9629 0.0107
-4.250 0.0894 0.02518 0.02277 -0.1393 0.9622 0.0118
-4.000 0.1292 0.02286 0.02027 -0.1424 0.9615 0.0148
-2.250 0.4082 0.00830 0.00381 -0.1640 0.9587 0.0146
-2.000 0.4459 0.00786 0.00333 -0.1661 0.9581 0.0155
-1.750 0.4724 0.00714 0.00251 -0.1657 0.9523 0.0168
-1.500 0.5067 0.00676 0.00207 -0.1670 0.9498 0.0174
-1.250 0.5416 0.00644 0.00170 -0.1684 0.9473 0.0187
-1.000 0.5758 0.00619 0.00141 -0.1696 0.9443 0.0190
-0.750 0.6027 0.00603 0.00122 -0.1692 0.9364 0.0197
-0.500 0.6395 0.00569 0.00102 -0.1712 0.9322 0.0754
-0.250 0.6725 0.00513 0.00101 -0.1726 0.9225 0.2950
0.000 0.7070 0.00473 0.00099 -0.1743 0.9116 0.4644
0.250 0.7406 0.00421 0.00109 -0.1758 0.8991 0.7322
0.500 0.7601 0.00377 0.00107 -0.1735 0.8827 1.0000
0.750 0.7886 0.00386 0.00107 -0.1735 0.8637 1.0000
1.000 0.8157 0.00398 0.00109 -0.1731 0.8410 1.0000
1.250 0.8419 0.00413 0.00113 -0.1727 0.8170 1.0000
1.500 0.8675 0.00431 0.00119 -0.1720 0.7900 1.0000
1.750 0.8920 0.00455 0.00128 -0.1712 0.7561 1.0000
2.000 0.9157 0.00484 0.00141 -0.1702 0.7153 1.0000
2.250 0.9389 0.00518 0.00155 -0.1691 0.6674 1.0000
2.500 0.9612 0.00563 0.00173 -0.1679 0.6076 1.0000
2.750 0.9790 0.00658 0.00207 -0.1660 0.4804 1.0000
3.000 0.9990 0.00746 0.00242 -0.1646 0.3681 1.0000
3.250 1.0210 0.00820 0.00275 -0.1637 0.2833 1.0000
3.500 1.0429 0.00896 0.00314 -0.1627 0.2014 1.0000
3.750 1.0640 0.00989 0.00359 -0.1617 0.1124 1.0000
4.000 1.0858 0.01075 0.00407 -0.1607 0.0436 1.0000
4.250 1.1084 0.01158 0.00467 -0.1596 0.0075 1.0000
4.500 1.1334 0.01206 0.00528 -0.1589 0.0059 1.0000
4.750 1.1582 0.01254 0.00585 -0.1581 0.0057 1.0000
5.000 1.1823 0.01314 0.00655 -0.1573 0.0056 1.0000
5.250 1.2055 0.01388 0.00741 -0.1562 0.0056 1.0000
5.500 1.2275 0.01485 0.00850 -0.1549 0.0057 1.0000
5.750 1.2489 0.01589 0.00965 -0.1535 0.0057 1.0000
6.000 1.2717 0.01668 0.01051 -0.1525 0.0054 1.0000
6.250 1.2936 0.01766 0.01159 -0.1513 0.0052 1.0000
6.500 1.3145 0.01898 0.01305 -0.1498 0.0052 1.0000
6.750 1.3358 0.02039 0.01459 -0.1484 0.0051 1.0000
7.000 1.3571 0.02199 0.01634 -0.1471 0.0049 1.0000
7.250 1.3784 0.02357 0.01808 -0.1457 0.0046 1.0000
7.500 1.3979 0.02629 0.02107 -0.1438 0.0045 1.0000
8.000 1.3613 0.03619 0.03261 -0.1279 0.0059 1.0000
8.250 1.3636 0.04052 0.03724 -0.1245 0.0059 1.0000
8.500 1.4340 0.04464 0.04115 -0.1306 0.0053 1.0000
8.750 1.4421 0.04772 0.04449 -0.1278 0.0049 1.0000
9.000 1.4421 0.05182 0.04892 -0.1242 0.0048 1.0000
9.250 1.4371 0.05615 0.05353 -0.1203 0.0046 1.0000
9.500 1.4256 0.06059 0.05822 -0.1161 0.0045 1.0000
9.750 1.4059 0.06414 0.06195 -0.1107 0.0044 1.0000
10.000 1.3841 0.06828 0.06628 -0.1065 0.0045 1.0000
10.250 1.3617 0.07304 0.07121 -0.1037 0.0044 1.0000
10.500 1.3372 0.07872 0.07706 -0.1027 0.0045 1.0000
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Polar data table (+)
Polar graphs
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