E71 (5.15%) (e71-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 500,000 Max Cl/Cd: 143.58 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e71-il-500000-n5.txt Download as CSV file: xf-e71-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3286 0.09736 0.09509 -0.0351 0.9933 0.0066
-7.750 -0.3205 0.09324 0.09097 -0.0371 0.9912 0.0064
-7.500 -0.3101 0.08946 0.08721 -0.0400 0.9886 0.0063
-7.250 -0.2982 0.08573 0.08348 -0.0432 0.9860 0.0062
-7.000 -0.2837 0.08193 0.07969 -0.0474 0.9836 0.0061
-6.750 -0.2670 0.07744 0.07521 -0.0527 0.9795 0.0064
-6.500 -0.2459 0.07294 0.07073 -0.0594 0.9748 0.0068
-6.250 -0.2285 0.06853 0.06631 -0.0649 0.9723 0.0076
-6.000 -0.2023 0.06504 0.06281 -0.0709 0.9706 0.0082
-5.750 -0.1823 0.06126 0.05902 -0.0760 0.9656 0.0086
-5.500 -0.1469 0.05840 0.05613 -0.0833 0.9621 0.0129
-5.250 -0.1102 0.05301 0.05069 -0.0929 0.9597 0.0130
-5.000 -0.0695 0.04561 0.04319 -0.1054 0.9581 0.0110
-4.750 -0.0229 0.03856 0.03597 -0.1172 0.9553 0.0105
-4.500 0.0259 0.03112 0.02825 -0.1277 0.9519 0.0107
-4.250 0.0766 0.02465 0.02134 -0.1361 0.9508 0.0115
-4.000 0.1193 0.02088 0.01718 -0.1409 0.9498 0.0122
-3.500 0.1985 0.01588 0.01137 -0.1477 0.9479 0.0125
-3.250 0.2368 0.01388 0.00898 -0.1504 0.9471 0.0121
-3.000 0.2734 0.01243 0.00725 -0.1525 0.9462 0.0118
-2.750 0.3091 0.01134 0.00596 -0.1542 0.9453 0.0117
-2.500 0.3399 0.01053 0.00501 -0.1549 0.9422 0.0115
-2.250 0.3699 0.00988 0.00425 -0.1553 0.9383 0.0116
-2.000 0.4033 0.00928 0.00357 -0.1565 0.9358 0.0117
-1.750 0.4380 0.00878 0.00300 -0.1579 0.9335 0.0121
-1.500 0.4712 0.00842 0.00259 -0.1590 0.9298 0.0130
-1.250 0.5020 0.00812 0.00223 -0.1596 0.9235 0.0148
-1.000 0.5395 0.00785 0.00189 -0.1615 0.9197 0.0168
-0.750 0.5723 0.00766 0.00169 -0.1625 0.9127 0.0211
-0.500 0.6103 0.00739 0.00148 -0.1647 0.9063 0.0464
-0.250 0.6459 0.00711 0.00134 -0.1664 0.8959 0.1114
0.000 0.6827 0.00671 0.00130 -0.1686 0.8839 0.2589
0.250 0.7182 0.00633 0.00132 -0.1705 0.8685 0.4362
0.500 0.7489 0.00563 0.00152 -0.1712 0.8483 0.8031
1.000 0.7948 0.00554 0.00147 -0.1683 0.8015 1.0000
1.250 0.8213 0.00572 0.00152 -0.1679 0.7739 1.0000
1.500 0.8465 0.00596 0.00159 -0.1672 0.7392 1.0000
1.750 0.8705 0.00627 0.00170 -0.1662 0.6983 1.0000
2.000 0.8937 0.00663 0.00188 -0.1652 0.6522 1.0000
2.250 0.9160 0.00707 0.00207 -0.1640 0.5970 1.0000
2.500 0.9376 0.00762 0.00230 -0.1627 0.5308 1.0000
2.750 0.9581 0.00834 0.00261 -0.1613 0.4474 1.0000
3.000 0.9739 0.00975 0.00314 -0.1594 0.2813 1.0000
3.250 0.9942 0.01076 0.00359 -0.1583 0.1754 1.0000
3.500 1.0165 0.01153 0.00399 -0.1574 0.1073 1.0000
3.750 1.0397 0.01221 0.00445 -0.1567 0.0595 1.0000
4.000 1.0633 0.01282 0.00490 -0.1560 0.0269 1.0000
4.250 1.0869 0.01346 0.00543 -0.1552 0.0073 1.0000
4.500 1.1120 0.01386 0.00588 -0.1546 0.0060 1.0000
4.750 1.1368 0.01431 0.00643 -0.1539 0.0051 1.0000
5.000 1.1611 0.01485 0.00708 -0.1531 0.0046 1.0000
5.250 1.1847 0.01551 0.00786 -0.1522 0.0044 1.0000
5.500 1.2075 0.01629 0.00875 -0.1511 0.0042 1.0000
5.750 1.2297 0.01716 0.00981 -0.1500 0.0041 1.0000
6.000 1.2508 0.01821 0.01098 -0.1486 0.0040 1.0000
6.250 1.2686 0.01993 0.01289 -0.1466 0.0036 1.0000
6.500 1.2892 0.02122 0.01432 -0.1453 0.0032 1.0000
6.750 1.3112 0.02217 0.01538 -0.1442 0.0030 1.0000
7.000 1.3321 0.02351 0.01688 -0.1429 0.0029 1.0000
7.250 1.3526 0.02502 0.01858 -0.1415 0.0027 1.0000
7.500 1.3726 0.02674 0.02050 -0.1401 0.0025 1.0000
7.750 1.3917 0.02873 0.02275 -0.1385 0.0023 1.0000
8.000 1.4090 0.03110 0.02546 -0.1366 0.0022 1.0000
8.250 1.4242 0.03376 0.02845 -0.1345 0.0021 1.0000
8.500 1.4364 0.03680 0.03185 -0.1320 0.0020 1.0000
8.750 1.4444 0.04036 0.03581 -0.1290 0.0020 1.0000
9.000 1.4477 0.04427 0.04013 -0.1256 0.0020 1.0000
9.250 1.4446 0.04869 0.04496 -0.1215 0.0020 1.0000
9.500 1.4355 0.05323 0.04986 -0.1171 0.0020 1.0000
9.750 1.4181 0.05717 0.05408 -0.1117 0.0021 1.0000
10.000 1.3978 0.06145 0.05862 -0.1070 0.0021 1.0000
10.250 1.3764 0.06622 0.06363 -0.1036 0.0021 1.0000
10.500 1.3550 0.07140 0.06902 -0.1017 0.0021 1.0000
10.750 1.3321 0.07743 0.07525 -0.1016 0.0021 1.0000
11.000 1.3096 0.08422 0.08223 -0.1033 0.0021 1.0000
11.250 1.2876 0.09219 0.09036 -0.1074 0.0022 1.0000
11.500 1.2662 0.10210 0.10043 -0.1142 0.0022 1.0000
11.750 1.2441 0.11659 0.11507 -0.1249 0.0022 1.0000
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Polar data table (+)
Polar graphs
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