E63 (4.25%) (e63-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 200,000 Max Cl/Cd: 112.53 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e63-il-200000.txt Download as CSV file: xf-e63-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E63 (4.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.750 -0.3756 0.09534 0.09227 -0.0145 1.0000 0.0167
-5.500 -0.3745 0.09181 0.08876 -0.0118 1.0000 0.0173
-5.250 -0.3710 0.08899 0.08597 -0.0112 1.0000 0.0178
-5.000 -0.3657 0.08623 0.08323 -0.0116 1.0000 0.0186
-4.750 -0.3576 0.08345 0.08048 -0.0131 1.0000 0.0192
-4.500 -0.3467 0.08051 0.07756 -0.0153 1.0000 0.0200
-4.250 -0.3324 0.07739 0.07445 -0.0185 1.0000 0.0210
-4.000 -0.3109 0.07385 0.07090 -0.0234 0.9996 0.0224
-3.750 -0.2080 0.06858 0.06542 -0.0511 0.9955 0.0269
-3.500 -0.1748 0.06124 0.05807 -0.0588 0.9924 0.0280
-3.250 -0.1508 0.05763 0.05443 -0.0611 0.9887 0.0298
-3.000 -0.1023 0.05344 0.05015 -0.0702 0.9863 0.0328
-2.750 -0.0258 0.04831 0.04478 -0.0861 0.9854 0.0383
-2.500 0.0476 0.04201 0.03819 -0.1008 0.9854 0.0413
-2.250 0.0864 0.03910 0.03525 -0.1056 0.9828 0.0454
-2.000 0.1623 0.03438 0.03001 -0.1184 0.9835 0.0550
-1.750 0.2042 0.03192 0.02746 -0.1230 0.9805 0.0624
-1.500 0.2578 0.02912 0.02436 -0.1298 0.9793 0.0748
-1.250 0.3106 0.02684 0.02170 -0.1360 0.9781 0.0973
-1.000 0.3754 0.02246 0.01634 -0.1410 0.9805 0.0367
-0.750 0.4232 0.02042 0.01368 -0.1442 0.9798 0.0281
-0.500 0.4659 0.01917 0.01227 -0.1472 0.9779 0.0323
-0.250 0.5093 0.01832 0.01131 -0.1501 0.9757 0.0369
0.000 0.5554 0.01760 0.01051 -0.1537 0.9738 0.0445
0.250 0.5940 0.01537 0.01046 -0.1561 0.9733 1.0000
0.500 0.6292 0.01534 0.01024 -0.1577 0.9653 1.0000
0.750 0.6717 0.01534 0.01007 -0.1607 0.9611 1.0000
1.000 0.7075 0.01522 0.00986 -0.1623 0.9529 1.0000
1.250 0.7470 0.01507 0.00965 -0.1646 0.9470 1.0000
1.500 0.7858 0.01485 0.00940 -0.1667 0.9399 1.0000
1.750 0.8236 0.01458 0.00916 -0.1684 0.9321 1.0000
2.000 0.8658 0.01416 0.00876 -0.1710 0.9260 1.0000
2.250 0.9018 0.01379 0.00843 -0.1722 0.9166 1.0000
2.500 0.9477 0.01310 0.00781 -0.1753 0.9113 1.0000
2.750 0.9828 0.01257 0.00743 -0.1761 0.9001 1.0000
3.000 1.0198 0.01200 0.00696 -0.1772 0.8880 1.0000
3.250 1.0606 0.01138 0.00644 -0.1790 0.8730 1.0000
3.500 1.1043 0.01085 0.00602 -0.1815 0.8495 1.0000
3.750 1.1602 0.01031 0.00548 -0.1865 0.8037 1.0000
4.000 1.1982 0.01082 0.00532 -0.1872 0.6581 1.0000
4.250 1.2143 0.01176 0.00576 -0.1843 0.5597 1.0000
4.500 1.2286 0.01279 0.00634 -0.1814 0.4677 1.0000
4.750 1.2385 0.01431 0.00711 -0.1780 0.3371 1.0000
5.000 1.2506 0.01606 0.00805 -0.1754 0.2016 1.0000
5.250 1.2603 0.01877 0.00971 -0.1725 0.0486 1.0000
5.500 1.2782 0.02041 0.01135 -0.1703 0.0330 1.0000
5.750 1.2970 0.02180 0.01291 -0.1682 0.0299 1.0000
6.000 1.3157 0.02328 0.01453 -0.1662 0.0283 1.0000
6.250 1.3351 0.02503 0.01641 -0.1643 0.0273 1.0000
6.500 1.3572 0.02708 0.01858 -0.1628 0.0266 1.0000
6.750 1.3797 0.02880 0.02040 -0.1618 0.0242 1.0000
7.000 1.4046 0.03158 0.02340 -0.1610 0.0230 1.0000
7.250 1.4308 0.03491 0.02706 -0.1601 0.0229 1.0000
7.500 1.4548 0.03851 0.03118 -0.1583 0.0237 1.0000
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Polar data table (+)
Polar graphs
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