E62 (5.62%) (e62-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 50,000 Max Cl/Cd: 47.67 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e62-il-50000-n5.txt Download as CSV file: xf-e62-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3550 0.10450 0.09817 -0.0218 1.0000 0.0799
-6.500 -0.3589 0.10295 0.09672 -0.0217 1.0000 0.0819
-6.250 -0.3628 0.10197 0.09585 -0.0237 1.0000 0.0836
-6.000 -0.3613 0.10085 0.09481 -0.0284 1.0000 0.0844
-5.750 -0.3588 0.09684 0.09089 -0.0262 1.0000 0.0854
-5.500 -0.3559 0.09333 0.08741 -0.0229 1.0000 0.0873
-5.250 -0.3520 0.09062 0.08475 -0.0223 1.0000 0.0898
-5.000 -0.3463 0.08804 0.08221 -0.0234 1.0000 0.0931
-4.750 -0.3225 0.08601 0.08013 -0.0357 1.0000 0.0984
-4.500 -0.3179 0.08221 0.07640 -0.0339 1.0000 0.0997
-4.250 -0.3127 0.07907 0.07330 -0.0318 1.0000 0.1020
-4.000 -0.2998 0.07613 0.07030 -0.0333 1.0000 0.1060
-3.750 -0.2644 0.07211 0.06620 -0.0430 0.9981 0.1146
-3.500 -0.2222 0.06807 0.06203 -0.0523 0.9937 0.1280
-3.250 -0.1981 0.06462 0.05856 -0.0540 0.9892 0.1362
-3.000 -0.1082 0.05564 0.04897 -0.0752 0.9874 0.0726
-2.750 -0.0606 0.05070 0.04376 -0.0822 0.9851 0.0543
-2.500 0.0166 0.04439 0.03655 -0.0959 0.9844 0.0450
-2.250 0.0600 0.04078 0.03270 -0.1015 0.9816 0.0436
-2.000 0.1104 0.03735 0.02869 -0.1078 0.9794 0.0425
-1.750 0.1597 0.03446 0.02518 -0.1131 0.9772 0.0419
-1.500 0.2059 0.03217 0.02225 -0.1172 0.9748 0.0422
-1.250 0.2485 0.03067 0.02007 -0.1202 0.9720 0.0449
-1.000 0.2840 0.02944 0.01865 -0.1223 0.9673 0.0507
-0.750 0.3213 0.02854 0.01730 -0.1240 0.9632 0.0549
-0.500 0.3597 0.02779 0.01624 -0.1259 0.9596 0.0620
-0.250 0.3942 0.02722 0.01552 -0.1274 0.9538 0.0836
0.000 0.4293 0.02464 0.01551 -0.1295 0.9522 0.6917
0.250 0.4556 0.02461 0.01508 -0.1291 0.9427 1.0000
0.500 0.4913 0.02500 0.01499 -0.1309 0.9364 1.0000
0.750 0.5210 0.02535 0.01504 -0.1317 0.9280 1.0000
1.000 0.5582 0.02571 0.01512 -0.1337 0.9222 1.0000
1.250 0.5862 0.02606 0.01529 -0.1342 0.9128 1.0000
1.500 0.6180 0.02640 0.01548 -0.1353 0.9048 1.0000
1.750 0.6526 0.02668 0.01565 -0.1368 0.8971 1.0000
2.000 0.6814 0.02702 0.01592 -0.1372 0.8873 1.0000
2.250 0.7149 0.02726 0.01615 -0.1384 0.8789 1.0000
2.500 0.7483 0.02747 0.01636 -0.1395 0.8700 1.0000
2.750 0.7772 0.02775 0.01666 -0.1399 0.8592 1.0000
3.000 0.8089 0.02793 0.01691 -0.1406 0.8491 1.0000
3.250 0.8478 0.02784 0.01697 -0.1422 0.8409 1.0000
3.500 0.8773 0.02796 0.01720 -0.1423 0.8287 1.0000
3.750 0.9082 0.02799 0.01738 -0.1425 0.8163 1.0000
4.000 0.9403 0.02791 0.01747 -0.1428 0.8037 1.0000
4.250 0.9737 0.02772 0.01756 -0.1430 0.7903 1.0000
4.500 1.0081 0.02742 0.01750 -0.1433 0.7757 1.0000
4.750 1.0442 0.02700 0.01735 -0.1436 0.7598 1.0000
5.000 1.0781 0.02660 0.01731 -0.1434 0.7410 1.0000
5.250 1.1090 0.02624 0.01723 -0.1426 0.7180 1.0000
5.500 1.1383 0.02589 0.01718 -0.1415 0.6904 1.0000
5.750 1.1661 0.02561 0.01717 -0.1399 0.6563 1.0000
6.000 1.1913 0.02547 0.01725 -0.1379 0.6126 1.0000
6.250 1.2147 0.02548 0.01744 -0.1356 0.5544 1.0000
6.500 1.2336 0.02595 0.01763 -0.1324 0.4657 1.0000
6.750 1.2362 0.02768 0.01845 -0.1276 0.3404 1.0000
7.000 1.2309 0.03033 0.02002 -0.1230 0.2127 1.0000
7.250 1.2303 0.03336 0.02204 -0.1198 0.1036 1.0000
7.500 1.2370 0.03615 0.02449 -0.1170 0.0621 1.0000
7.750 1.2463 0.03860 0.02699 -0.1143 0.0494 1.0000
8.000 1.2562 0.04092 0.02942 -0.1119 0.0435 1.0000
8.250 1.2697 0.04316 0.03203 -0.1096 0.0398 1.0000
8.500 1.2855 0.04535 0.03449 -0.1079 0.0357 1.0000
8.750 1.2999 0.04791 0.03713 -0.1063 0.0323 1.0000
9.000 1.3249 0.05067 0.04025 -0.1056 0.0300 1.0000
9.250 1.3529 0.05408 0.04412 -0.1052 0.0288 1.0000
9.500 1.3734 0.05790 0.04844 -0.1042 0.0281 1.0000
9.750 1.3842 0.06181 0.05285 -0.1023 0.0277 1.0000
10.000 1.3869 0.06575 0.05725 -0.0996 0.0274 1.0000
10.250 1.3831 0.06972 0.06165 -0.0967 0.0273 1.0000
10.500 1.3744 0.07379 0.06612 -0.0937 0.0273 1.0000
10.750 1.3619 0.07803 0.07074 -0.0911 0.0273 1.0000
11.000 1.3463 0.08261 0.07565 -0.0891 0.0274 1.0000
11.250 1.3286 0.08755 0.08090 -0.0880 0.0275 1.0000
11.500 1.3095 0.09293 0.08656 -0.0879 0.0276 1.0000
11.750 1.2892 0.09886 0.09275 -0.0890 0.0278 1.0000
12.000 1.2683 0.10546 0.09957 -0.0913 0.0280 1.0000
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Polar data table (+)
Polar graphs
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