E62 (5.62%) (e62-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 100,000 Max Cl/Cd: 74.69 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e62-il-100000.txt Download as CSV file: xf-e62-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E62 (5.62%)
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3524 0.10313 0.09862 -0.0203 1.0000 0.0518
-6.750 -0.3597 0.10173 0.09730 -0.0183 1.0000 0.0529
-6.500 -0.3679 0.10045 0.09610 -0.0163 1.0000 0.0543
-6.250 -0.3723 0.09893 0.09465 -0.0159 1.0000 0.0557
-6.000 -0.3749 0.09764 0.09343 -0.0172 1.0000 0.0570
-5.750 -0.3713 0.09666 0.09251 -0.0227 1.0000 0.0579
-5.500 -0.3556 0.09501 0.09085 -0.0319 1.0000 0.0584
-5.250 -0.3605 0.08993 0.08586 -0.0266 1.0000 0.0594
-5.000 -0.3623 0.08658 0.08255 -0.0215 1.0000 0.0608
-4.750 -0.3579 0.08384 0.07983 -0.0205 1.0000 0.0628
-4.500 -0.3488 0.08108 0.07708 -0.0220 1.0000 0.0654
-4.250 -0.3312 0.07802 0.07398 -0.0269 1.0000 0.0692
-4.000 -0.2818 0.07344 0.06926 -0.0439 1.0000 0.0729
-3.750 -0.2830 0.07036 0.06625 -0.0394 1.0000 0.0745
-3.500 -0.2709 0.06758 0.06347 -0.0393 1.0000 0.0777
-3.250 -0.2069 0.06261 0.05823 -0.0567 1.0000 0.0871
-3.000 -0.2019 0.05980 0.05551 -0.0537 1.0000 0.0896
-2.750 -0.1459 0.05571 0.05115 -0.0660 1.0000 0.1014
-2.500 -0.1346 0.05312 0.04863 -0.0645 1.0000 0.1051
-2.250 -0.0809 0.04933 0.04464 -0.0738 0.9969 0.1194
-2.000 -0.0152 0.04567 0.04065 -0.0855 0.9930 0.1446
-1.750 0.0328 0.04303 0.03787 -0.0920 0.9886 0.1728
-1.250 0.1876 0.03260 0.02555 -0.1128 0.9859 0.0852
-1.000 0.2428 0.02926 0.02157 -0.1179 0.9845 0.0672
-0.750 0.2882 0.02736 0.01900 -0.1209 0.9803 0.0613
-0.500 0.3309 0.02628 0.01760 -0.1235 0.9761 0.0609
-0.250 0.3748 0.02559 0.01683 -0.1266 0.9727 0.0678
0.000 0.4105 0.02505 0.01628 -0.1285 0.9660 0.0831
0.250 0.4490 0.02222 0.01578 -0.1302 0.9635 1.0000
0.500 0.4857 0.02267 0.01580 -0.1323 0.9561 1.0000
0.750 0.5243 0.02307 0.01591 -0.1347 0.9490 1.0000
1.000 0.5570 0.02342 0.01606 -0.1361 0.9400 1.0000
1.250 0.5977 0.02375 0.01622 -0.1388 0.9334 1.0000
1.500 0.6313 0.02402 0.01638 -0.1403 0.9243 1.0000
1.750 0.6644 0.02429 0.01659 -0.1416 0.9151 1.0000
2.000 0.7088 0.02438 0.01662 -0.1447 0.9089 1.0000
2.250 0.7397 0.02455 0.01678 -0.1455 0.8981 1.0000
2.500 0.7740 0.02465 0.01690 -0.1467 0.8881 1.0000
2.750 0.8214 0.02438 0.01670 -0.1500 0.8819 1.0000
3.000 0.8537 0.02436 0.01674 -0.1506 0.8704 1.0000
3.250 0.8895 0.02417 0.01664 -0.1517 0.8595 1.0000
3.500 0.9336 0.02359 0.01618 -0.1539 0.8507 1.0000
3.750 0.9810 0.02269 0.01550 -0.1563 0.8421 1.0000
4.000 1.0219 0.02193 0.01492 -0.1576 0.8304 1.0000
4.250 1.0679 0.02090 0.01410 -0.1594 0.8184 1.0000
4.500 1.1136 0.01976 0.01319 -0.1610 0.8042 1.0000
4.750 1.1601 0.01856 0.01230 -0.1625 0.7867 1.0000
5.000 1.1942 0.01788 0.01183 -0.1620 0.7616 1.0000
5.250 1.2268 0.01718 0.01127 -0.1609 0.7261 1.0000
5.500 1.2494 0.01676 0.01084 -0.1577 0.6648 1.0000
5.750 1.2645 0.01693 0.01064 -0.1535 0.5666 1.0000
6.000 1.2695 0.01826 0.01101 -0.1484 0.4177 1.0000
6.250 1.2686 0.02046 0.01217 -0.1433 0.2662 1.0000
6.500 1.2588 0.02454 0.01457 -0.1375 0.0795 1.0000
6.750 1.2656 0.02699 0.01684 -0.1336 0.0556 1.0000
7.000 1.2771 0.02882 0.01882 -0.1305 0.0491 1.0000
7.250 1.2896 0.03085 0.02086 -0.1278 0.0451 1.0000
7.500 1.3119 0.03383 0.02387 -0.1267 0.0426 1.0000
7.750 1.3416 0.03624 0.02650 -0.1264 0.0403 1.0000
8.000 1.3688 0.03869 0.02917 -0.1260 0.0372 1.0000
8.250 1.3985 0.04203 0.03282 -0.1258 0.0364 1.0000
8.500 1.4227 0.04601 0.03733 -0.1245 0.0370 1.0000
8.750 1.4391 0.05042 0.04235 -0.1222 0.0382 1.0000
9.000 1.4495 0.05515 0.04762 -0.1194 0.0398 1.0000
9.250 1.4556 0.06022 0.05313 -0.1166 0.0413 1.0000
9.500 1.4690 0.06691 0.06008 -0.1154 0.0436 1.0000
9.750 1.4445 0.07059 0.06482 -0.1075 0.0489 1.0000
10.000 1.3391 0.06855 0.06340 -0.0910 0.0474 1.0000
10.250 1.3107 0.07331 0.06849 -0.0863 0.0485 1.0000
10.500 1.2810 0.07849 0.07394 -0.0827 0.0492 1.0000
10.750 1.2507 0.08373 0.07943 -0.0804 0.0495 1.0000
11.000 1.2184 0.08918 0.08510 -0.0793 0.0495 1.0000
11.250 1.1825 0.09493 0.09107 -0.0794 0.0493 1.0000
11.500 1.1427 0.10039 0.09673 -0.0806 0.0486 1.0000
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Polar data table (+)
Polar graphs
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