E63 (4.25%) (e63-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 100,000 Max Cl/Cd: 77.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e63-il-100000.txt Download as CSV file: xf-e63-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3041 0.10888 0.10445 -0.0221 1.0000 0.0394
-7.750 -0.3095 0.10768 0.10331 -0.0216 1.0000 0.0395
-7.500 -0.3173 0.10679 0.10250 -0.0207 1.0000 0.0396
-7.250 -0.2925 0.09619 0.09189 -0.0186 1.0000 0.0426
-7.000 -0.2924 0.09360 0.08934 -0.0174 1.0000 0.0440
-6.750 -0.2942 0.09127 0.08705 -0.0162 1.0000 0.0454
-6.500 -0.2975 0.08914 0.08499 -0.0150 1.0000 0.0466
-6.250 -0.3025 0.08720 0.08310 -0.0135 1.0000 0.0477
-6.000 -0.3092 0.08546 0.08143 -0.0117 1.0000 0.0487
-5.750 -0.3152 0.08373 0.07976 -0.0105 1.0000 0.0497
-5.500 -0.3177 0.08192 0.07801 -0.0107 1.0000 0.0509
-5.250 -0.3175 0.08047 0.07661 -0.0129 1.0000 0.0520
-5.000 -0.3089 0.07932 0.07548 -0.0196 1.0000 0.0528
-4.750 -0.2892 0.07739 0.07352 -0.0289 1.0000 0.0532
-4.500 -0.2779 0.08293 0.07859 -0.0431 1.0000 0.0532
-4.250 -0.2933 0.07796 0.07375 -0.0338 1.0000 0.0544
-4.000 -0.2914 0.07475 0.07058 -0.0304 1.0000 0.0563
-3.750 -0.2757 0.07161 0.06743 -0.0323 1.0000 0.0594
-3.500 -0.1831 0.06698 0.06249 -0.0598 1.0000 0.0670
-3.250 -0.1914 0.06294 0.05860 -0.0533 1.0000 0.0684
-3.000 -0.1798 0.06006 0.05571 -0.0523 1.0000 0.0718
-2.750 -0.1098 0.05497 0.05038 -0.0688 1.0000 0.0820
-2.500 -0.0951 0.05223 0.04768 -0.0681 1.0000 0.0868
-2.250 -0.0410 0.04805 0.04333 -0.0783 1.0000 0.0985
-2.000 0.0068 0.04455 0.03969 -0.0860 1.0000 0.1127
-1.750 0.0643 0.04122 0.03609 -0.0957 1.0000 0.1377
-1.500 0.0975 0.03869 0.03351 -0.0987 1.0000 0.1560
-1.250 0.1419 0.03630 0.03098 -0.1044 1.0000 0.1943
-0.750 0.3138 0.02676 0.01934 -0.1268 1.0000 0.0725
-0.500 0.3609 0.02483 0.01679 -0.1299 1.0000 0.0615
-0.250 0.4006 0.02350 0.01507 -0.1318 1.0000 0.0596
0.000 0.4355 0.02267 0.01404 -0.1330 1.0000 0.0626
0.250 0.4702 0.02213 0.01350 -0.1345 1.0000 0.0784
0.500 0.5143 0.01941 0.01275 -0.1371 1.0000 1.0000
0.750 0.5365 0.02001 0.01305 -0.1366 1.0000 1.0000
1.000 0.5580 0.02066 0.01351 -0.1363 1.0000 1.0000
1.250 0.5788 0.02138 0.01409 -0.1359 1.0000 1.0000
1.500 0.6028 0.02217 0.01477 -0.1363 0.9981 1.0000
1.750 0.6498 0.02287 0.01535 -0.1408 0.9868 1.0000
2.000 0.6955 0.02334 0.01576 -0.1449 0.9754 1.0000
2.250 0.7400 0.02361 0.01602 -0.1486 0.9637 1.0000
2.500 0.7845 0.02371 0.01618 -0.1520 0.9517 1.0000
2.750 0.8297 0.02363 0.01616 -0.1554 0.9392 1.0000
3.000 0.8751 0.02336 0.01599 -0.1586 0.9263 1.0000
3.250 0.9212 0.02290 0.01566 -0.1616 0.9129 1.0000
3.500 0.9687 0.02217 0.01520 -0.1645 0.8991 1.0000
3.750 1.0177 0.02114 0.01440 -0.1672 0.8849 1.0000
4.000 1.0594 0.02012 0.01362 -0.1684 0.8663 1.0000
4.250 1.1088 0.01860 0.01240 -0.1703 0.8470 1.0000
4.500 1.1612 0.01708 0.01133 -0.1727 0.8171 1.0000
4.750 1.2127 0.01593 0.01036 -0.1747 0.7523 1.0000
5.000 1.2532 0.01618 0.00975 -0.1744 0.5716 1.0000
5.250 1.2628 0.01790 0.01053 -0.1702 0.4083 1.0000
5.500 1.2692 0.02013 0.01175 -0.1662 0.2448 1.0000
5.750 1.2687 0.02456 0.01462 -0.1612 0.0777 1.0000
6.000 1.2838 0.02660 0.01661 -0.1586 0.0583 1.0000
6.250 1.3006 0.02887 0.01893 -0.1562 0.0516 1.0000
6.500 1.3239 0.03115 0.02130 -0.1548 0.0476 1.0000
6.750 1.3527 0.03411 0.02431 -0.1545 0.0450 1.0000
7.000 1.3863 0.03820 0.02859 -0.1548 0.0439 1.0000
7.250 1.4143 0.04214 0.03304 -0.1539 0.0440 1.0000
7.500 1.4328 0.04654 0.03803 -0.1518 0.0426 1.0000
7.750 1.4476 0.05014 0.04227 -0.1488 0.0418 1.0000
8.000 1.4608 0.05678 0.04934 -0.1466 0.0430 1.0000
8.250 1.4650 0.06080 0.05458 -0.1406 0.0487 1.0000
8.500 1.4681 0.06795 0.06213 -0.1375 0.0533 1.0000
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Polar data table (+)
Polar graphs
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