E471 (6.25%) (e471-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.02 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e471-il-1000000-n5.txt Download as CSV file: xf-e471-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3006 0.10779 0.10608 -0.0477 0.9928 0.0032
-9.500 -0.2924 0.10387 0.10217 -0.0500 0.9915 0.0030
-9.250 -0.2834 0.09989 0.09820 -0.0525 0.9900 0.0029
-9.000 -0.2726 0.09635 0.09465 -0.0552 0.9885 0.0031
-8.750 -0.2618 0.09238 0.09069 -0.0584 0.9870 0.0030
-8.500 -0.2489 0.08884 0.08715 -0.0617 0.9856 0.0034
-8.250 -0.2358 0.08480 0.08312 -0.0656 0.9843 0.0031
-8.000 -0.2208 0.08080 0.07912 -0.0700 0.9831 0.0036
-7.750 -0.2143 0.07698 0.07531 -0.0724 0.9789 0.0040
-7.250 -0.1252 0.04988 0.04829 -0.0839 0.9641 0.0055
-6.750 -0.1490 0.05743 0.05575 -0.0979 0.9608 0.0054
-6.500 -0.1174 0.05247 0.05076 -0.1076 0.9582 0.0056
-6.250 -0.0874 0.04798 0.04623 -0.1160 0.9534 0.0058
-6.000 -0.0542 0.04300 0.04118 -0.1251 0.9477 0.0063
-5.750 -0.0086 0.03516 0.03316 -0.1384 0.9440 0.0068
-5.500 0.0298 0.02662 0.02429 -0.1478 0.9361 0.0072
-5.250 0.0702 0.01902 0.01611 -0.1547 0.9315 0.0077
-5.000 0.1028 0.01560 0.01225 -0.1574 0.9258 0.0080
-4.750 0.1360 0.01304 0.00926 -0.1595 0.9205 0.0080
-4.500 0.1676 0.01146 0.00737 -0.1607 0.9154 0.0083
-4.250 0.1976 0.01056 0.00626 -0.1614 0.9093 0.0087
-4.000 0.2273 0.01014 0.00572 -0.1619 0.9037 0.0092
-3.250 0.3147 0.00802 0.00318 -0.1632 0.8846 0.0113
-3.000 0.3436 0.00766 0.00273 -0.1635 0.8783 0.0117
-2.750 0.3721 0.00734 0.00236 -0.1637 0.8718 0.0120
-2.500 0.4006 0.00712 0.00207 -0.1639 0.8652 0.0127
-2.250 0.4291 0.00687 0.00174 -0.1641 0.8577 0.0128
-2.000 0.4575 0.00668 0.00147 -0.1641 0.8495 0.0125
-1.750 0.4856 0.00654 0.00125 -0.1641 0.8402 0.0124
-1.500 0.5135 0.00644 0.00108 -0.1641 0.8307 0.0123
-1.250 0.5412 0.00637 0.00094 -0.1640 0.8208 0.0123
-0.750 0.5962 0.00631 0.00076 -0.1638 0.7993 0.0126
-0.500 0.6234 0.00631 0.00070 -0.1636 0.7874 0.0134
-0.250 0.6506 0.00631 0.00066 -0.1634 0.7751 0.0167
0.000 0.6784 0.00616 0.00066 -0.1635 0.7618 0.0993
0.250 0.7057 0.00607 0.00070 -0.1635 0.7463 0.1758
0.500 0.7330 0.00591 0.00078 -0.1636 0.7286 0.3026
0.750 0.7609 0.00563 0.00093 -0.1640 0.7092 0.5095
1.000 0.7878 0.00549 0.00107 -0.1640 0.6881 0.6624
1.250 0.8134 0.00548 0.00119 -0.1635 0.6623 0.7587
1.500 0.8361 0.00550 0.00133 -0.1624 0.6308 0.8604
2.000 0.8778 0.00594 0.00157 -0.1593 0.5431 1.0000
2.250 0.9012 0.00638 0.00176 -0.1585 0.4888 1.0000
2.500 0.9248 0.00682 0.00196 -0.1577 0.4374 1.0000
2.750 0.9485 0.00728 0.00218 -0.1570 0.3868 1.0000
3.000 0.9709 0.00787 0.00246 -0.1562 0.3205 1.0000
3.250 0.9892 0.00893 0.00294 -0.1547 0.2012 1.0000
3.500 1.0115 0.00957 0.00327 -0.1538 0.1408 1.0000
3.750 1.0350 0.01008 0.00358 -0.1531 0.1008 1.0000
4.000 1.0573 0.01073 0.00397 -0.1522 0.0524 1.0000
4.250 1.0801 0.01132 0.00437 -0.1514 0.0184 1.0000
4.500 1.1041 0.01179 0.00475 -0.1507 0.0061 1.0000
4.750 1.1292 0.01209 0.00509 -0.1502 0.0045 1.0000
5.000 1.1540 0.01243 0.00550 -0.1496 0.0036 1.0000
5.250 1.1784 0.01283 0.00598 -0.1489 0.0033 1.0000
5.500 1.2026 0.01323 0.00642 -0.1483 0.0032 1.0000
5.750 1.2267 0.01363 0.00685 -0.1476 0.0030 1.0000
6.000 1.2505 0.01404 0.00731 -0.1470 0.0027 1.0000
6.250 1.2737 0.01455 0.00787 -0.1461 0.0025 1.0000
6.500 1.2964 0.01511 0.00853 -0.1452 0.0024 1.0000
6.750 1.3188 0.01570 0.00918 -0.1443 0.0022 1.0000
7.000 1.3407 0.01632 0.00987 -0.1433 0.0020 1.0000
7.250 1.3624 0.01697 0.01058 -0.1422 0.0019 1.0000
7.500 1.3835 0.01766 0.01134 -0.1411 0.0018 1.0000
7.750 1.4033 0.01851 0.01227 -0.1398 0.0016 1.0000
8.000 1.4149 0.02058 0.01455 -0.1370 0.0014 1.0000
8.500 1.4509 0.02280 0.01700 -0.1338 0.0013 1.0000
8.750 1.4680 0.02403 0.01840 -0.1321 0.0013 1.0000
9.000 1.4840 0.02542 0.01994 -0.1302 0.0012 1.0000
9.250 1.4985 0.02703 0.02172 -0.1282 0.0012 1.0000
9.500 1.5115 0.02880 0.02368 -0.1259 0.0012 1.0000
9.750 1.5221 0.03083 0.02594 -0.1234 0.0012 1.0000
10.000 1.5284 0.03295 0.02828 -0.1201 0.0012 1.0000
10.250 1.5305 0.03519 0.03075 -0.1164 0.0012 1.0000
10.500 1.5295 0.03763 0.03342 -0.1124 0.0012 1.0000
10.750 1.5254 0.04033 0.03637 -0.1083 0.0011 1.0000
11.000 1.5185 0.04332 0.03961 -0.1043 0.0011 1.0000
11.250 1.5081 0.04673 0.04326 -0.1005 0.0011 1.0000
11.500 1.4959 0.05042 0.04718 -0.0973 0.0011 1.0000
11.750 1.4822 0.05444 0.05143 -0.0946 0.0011 1.0000
12.000 1.4667 0.05892 0.05612 -0.0927 0.0012 1.0000
12.250 1.4479 0.06420 0.06163 -0.0917 0.0012 1.0000
12.500 1.4287 0.07000 0.06762 -0.0917 0.0012 1.0000
12.750 1.4090 0.07647 0.07428 -0.0930 0.0012 1.0000
13.000 1.3861 0.08429 0.08230 -0.0959 0.0012 1.0000
13.250 1.3663 0.09257 0.09074 -0.1000 0.0012 1.0000
13.500 1.3455 0.10239 0.10072 -0.1060 0.0012 1.0000
13.750 1.3249 0.11371 0.11220 -0.1134 0.0012 1.0000
14.000 1.3040 0.12683 0.12545 -0.1220 0.0012 1.0000
14.250 1.2813 0.14175 0.14050 -0.1311 0.0012 1.0000
14.500 1.2579 0.15702 0.15585 -0.1395 0.0012 1.0000
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Polar data table (+)
Polar graphs
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