E63 (4.25%) (e63-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 100,000 Max Cl/Cd: 77.65 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e63-il-100000-n5.txt Download as CSV file: xf-e63-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3661 0.11169 0.10686 -0.0194 1.0000 0.0254
-7.250 -0.3715 0.11068 0.10593 -0.0184 1.0000 0.0255
-7.000 -0.3763 0.10938 0.10470 -0.0175 1.0000 0.0256
-6.750 -0.3758 0.10765 0.10303 -0.0182 1.0000 0.0257
-6.500 -0.3724 0.10551 0.10095 -0.0195 1.0000 0.0258
-6.250 -0.3668 0.10309 0.09858 -0.0212 1.0000 0.0258
-6.000 -0.3657 0.09850 0.09406 -0.0189 1.0000 0.0262
-5.750 -0.3635 0.09462 0.09021 -0.0156 1.0000 0.0269
-5.500 -0.3598 0.09178 0.08741 -0.0149 1.0000 0.0276
-5.250 -0.3546 0.08912 0.08479 -0.0153 1.0000 0.0283
-5.000 -0.3479 0.08642 0.08212 -0.0163 1.0000 0.0291
-4.750 -0.3349 0.08334 0.07906 -0.0190 0.9993 0.0302
-4.500 -0.3038 0.07925 0.07495 -0.0265 0.9954 0.0320
-4.250 -0.2656 0.07502 0.07067 -0.0364 0.9914 0.0344
-4.000 -0.1902 0.06993 0.06539 -0.0583 0.9875 0.0360
-3.750 -0.1644 0.06482 0.06030 -0.0624 0.9850 0.0368
-3.500 -0.1448 0.06114 0.05662 -0.0637 0.9816 0.0381
-3.250 -0.1073 0.05713 0.05247 -0.0703 0.9783 0.0402
-3.000 -0.0535 0.05255 0.04775 -0.0812 0.9762 0.0439
-2.500 0.0794 0.04109 0.03566 -0.1058 0.9755 0.0247
-2.250 0.1469 0.03533 0.02944 -0.1169 0.9767 0.0194
-2.000 0.1987 0.03220 0.02598 -0.1239 0.9764 0.0211
-1.750 0.2547 0.02899 0.02221 -0.1308 0.9765 0.0230
-1.500 0.3078 0.02607 0.01866 -0.1364 0.9767 0.0219
-1.250 0.3556 0.02387 0.01584 -0.1404 0.9763 0.0214
-1.000 0.3987 0.02229 0.01378 -0.1434 0.9751 0.0219
-0.750 0.4393 0.02119 0.01242 -0.1458 0.9735 0.0231
-0.500 0.4759 0.02041 0.01147 -0.1476 0.9694 0.0250
-0.250 0.5145 0.01985 0.01084 -0.1500 0.9656 0.0376
0.000 0.5601 0.01810 0.01060 -0.1544 0.9657 0.5315
0.500 0.6175 0.01733 0.01004 -0.1541 0.9516 1.0000
0.750 0.6505 0.01737 0.00989 -0.1552 0.9437 1.0000
1.000 0.6884 0.01735 0.00972 -0.1572 0.9376 1.0000
1.250 0.7198 0.01734 0.00964 -0.1579 0.9281 1.0000
1.500 0.7543 0.01728 0.00956 -0.1591 0.9197 1.0000
1.750 0.7911 0.01713 0.00937 -0.1607 0.9118 1.0000
2.250 0.8558 0.01685 0.00914 -0.1619 0.8898 1.0000
2.500 0.8892 0.01661 0.00896 -0.1626 0.8780 1.0000
2.750 0.9226 0.01634 0.00883 -0.1632 0.8644 1.0000
3.000 0.9567 0.01606 0.00864 -0.1639 0.8487 1.0000
3.250 0.9950 0.01568 0.00836 -0.1652 0.8307 1.0000
3.500 1.0322 0.01537 0.00817 -0.1664 0.8057 1.0000
3.750 1.0764 0.01502 0.00803 -0.1688 0.7717 1.0000
4.000 1.1243 0.01478 0.00779 -0.1719 0.7176 1.0000
4.250 1.1647 0.01500 0.00782 -0.1736 0.6410 1.0000
4.500 1.1881 0.01607 0.00814 -0.1720 0.5054 1.0000
4.750 1.2000 0.01774 0.00887 -0.1688 0.3571 1.0000
5.000 1.2159 0.01915 0.00984 -0.1668 0.2572 1.0000
5.250 1.2318 0.02078 0.01086 -0.1651 0.1566 1.0000
5.500 1.2481 0.02252 0.01209 -0.1633 0.0743 1.0000
5.750 1.2656 0.02423 0.01362 -0.1614 0.0402 1.0000
6.000 1.2836 0.02582 0.01530 -0.1594 0.0326 1.0000
6.250 1.3021 0.02722 0.01697 -0.1575 0.0292 1.0000
6.500 1.3194 0.02874 0.01861 -0.1557 0.0246 1.0000
6.750 1.3358 0.03048 0.02054 -0.1536 0.0220 1.0000
7.000 1.3535 0.03239 0.02269 -0.1517 0.0208 1.0000
7.250 1.3729 0.03458 0.02511 -0.1500 0.0198 1.0000
7.500 1.3944 0.03715 0.02810 -0.1486 0.0190 1.0000
7.750 1.4168 0.04011 0.03142 -0.1474 0.0185 1.0000
8.000 1.4376 0.04351 0.03525 -0.1459 0.0181 1.0000
8.250 1.4543 0.04728 0.03953 -0.1438 0.0179 1.0000
8.500 1.4655 0.05149 0.04432 -0.1411 0.0178 1.0000
8.750 1.4714 0.05557 0.04892 -0.1379 0.0173 1.0000
9.000 1.4742 0.05858 0.05223 -0.1350 0.0160 1.0000
9.500 1.4556 0.06775 0.06215 -0.1272 0.0146 1.0000
9.750 1.4410 0.07134 0.06612 -0.1225 0.0144 1.0000
10.000 1.4229 0.07537 0.07050 -0.1182 0.0143 1.0000
10.250 1.4032 0.07990 0.07535 -0.1149 0.0143 1.0000
10.500 1.3831 0.08483 0.08055 -0.1129 0.0143 1.0000
10.750 1.3641 0.09005 0.08600 -0.1122 0.0144 1.0000
11.000 1.3436 0.09603 0.09220 -0.1130 0.0144 1.0000
11.250 1.3234 0.10272 0.09908 -0.1154 0.0144 1.0000
11.500 1.3036 0.11035 0.10689 -0.1196 0.0145 1.0000
11.750 1.2885 0.11804 0.11467 -0.1242 0.0148 1.0000
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Polar data table (+)
Polar graphs
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