E62 (5.62%) (e62-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 200,000 Max Cl/Cd: 107.6 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e62-il-200000.txt Download as CSV file: xf-e62-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3695 0.11232 0.10906 -0.0225 1.0000 0.0218
-7.500 -0.3773 0.11106 0.10786 -0.0206 1.0000 0.0218
-7.250 -0.3841 0.10964 0.10649 -0.0187 1.0000 0.0218
-7.000 -0.3873 0.10785 0.10475 -0.0182 1.0000 0.0219
-6.750 -0.3886 0.10578 0.10272 -0.0182 1.0000 0.0219
-6.500 -0.3939 0.10067 0.09768 -0.0160 1.0000 0.0224
-6.250 -0.3906 0.09709 0.09411 -0.0132 0.9996 0.0231
-6.000 -0.3686 0.09299 0.09000 -0.0171 0.9960 0.0240
-5.750 -0.3452 0.08902 0.08601 -0.0225 0.9912 0.0253
-5.500 -0.3174 0.08485 0.08183 -0.0295 0.9863 0.0267
-5.250 -0.2892 0.08058 0.07754 -0.0371 0.9801 0.0291
-5.000 -0.2269 0.07587 0.07273 -0.0571 0.9740 0.0319
-4.750 -0.1899 0.06944 0.06623 -0.0681 0.9687 0.0329
-4.500 -0.1843 0.06613 0.06295 -0.0649 0.9643 0.0346
-4.250 -0.1509 0.06232 0.05909 -0.0706 0.9613 0.0371
-4.000 -0.1139 0.05821 0.05491 -0.0782 0.9562 0.0401
-3.750 -0.0249 0.05274 0.04900 -0.0994 0.9526 0.0449
-3.500 -0.0005 0.04691 0.04324 -0.1032 0.9502 0.0470
-3.250 0.0362 0.04392 0.04018 -0.1077 0.9483 0.0506
-3.000 0.1089 0.03814 0.03388 -0.1215 0.9478 0.0599
-2.750 0.1322 0.03592 0.03171 -0.1225 0.9416 0.0629
-2.500 0.1861 0.03229 0.02765 -0.1300 0.9398 0.0745
-1.750 0.3422 0.02096 0.01437 -0.1445 0.9386 0.0346
-1.500 0.3833 0.01976 0.01298 -0.1473 0.9367 0.0394
-1.250 0.4260 0.01824 0.01114 -0.1498 0.9355 0.0369
-1.000 0.4574 0.01740 0.01023 -0.1504 0.9299 0.0371
-0.750 0.4952 0.01666 0.00943 -0.1524 0.9263 0.0396
-0.500 0.5365 0.01600 0.00870 -0.1549 0.9238 0.0498
-0.250 0.5785 0.01411 0.00870 -0.1586 0.9229 0.6512
0.000 0.5987 0.01352 0.00847 -0.1563 0.9150 1.0000
0.250 0.6376 0.01334 0.00811 -0.1584 0.9112 1.0000
0.500 0.6797 0.01305 0.00770 -0.1610 0.9089 1.0000
0.750 0.7078 0.01302 0.00758 -0.1610 0.9005 1.0000
1.000 0.7487 0.01267 0.00718 -0.1633 0.8975 1.0000
1.250 0.7934 0.01224 0.00670 -0.1663 0.8953 1.0000
1.500 0.8225 0.01213 0.00658 -0.1664 0.8863 1.0000
1.750 0.8653 0.01171 0.00615 -0.1690 0.8826 1.0000
2.000 0.8965 0.01156 0.00603 -0.1693 0.8734 1.0000
2.250 0.9391 0.01114 0.00562 -0.1719 0.8679 1.0000
2.500 0.9693 0.01102 0.00553 -0.1720 0.8567 1.0000
2.750 1.0010 0.01090 0.00544 -0.1724 0.8452 1.0000
3.000 1.0328 0.01079 0.00540 -0.1728 0.8324 1.0000
3.250 1.0635 0.01072 0.00536 -0.1729 0.8178 1.0000
3.500 1.0931 0.01070 0.00536 -0.1728 0.8018 1.0000
3.750 1.1219 0.01072 0.00540 -0.1725 0.7840 1.0000
4.000 1.1467 0.01082 0.00553 -0.1715 0.7622 1.0000
4.250 1.1714 0.01090 0.00564 -0.1702 0.7326 1.0000
4.500 1.1922 0.01108 0.00567 -0.1680 0.6852 1.0000
4.750 1.2103 0.01144 0.00582 -0.1655 0.6233 1.0000
5.000 1.2216 0.01228 0.00609 -0.1617 0.5188 1.0000
5.250 1.2291 0.01356 0.00671 -0.1577 0.4053 1.0000
5.500 1.2369 0.01506 0.00759 -0.1541 0.2920 1.0000
5.750 1.2446 0.01689 0.00866 -0.1509 0.1677 1.0000
6.000 1.2476 0.01963 0.01042 -0.1469 0.0383 1.0000
6.250 1.2639 0.02095 0.01182 -0.1445 0.0297 1.0000
6.500 1.2808 0.02206 0.01304 -0.1425 0.0255 1.0000
6.750 1.2914 0.02388 0.01495 -0.1395 0.0226 1.0000
7.000 1.3068 0.02525 0.01645 -0.1372 0.0219 1.0000
7.250 1.3226 0.02687 0.01822 -0.1350 0.0212 1.0000
7.500 1.3413 0.02879 0.02026 -0.1333 0.0207 1.0000
7.750 1.3650 0.03110 0.02273 -0.1324 0.0205 1.0000
8.000 1.3929 0.03397 0.02581 -0.1321 0.0207 1.0000
8.250 1.4203 0.03750 0.02967 -0.1317 0.0213 1.0000
8.500 1.4432 0.04237 0.03494 -0.1308 0.0222 1.0000
8.750 1.4657 0.04532 0.03813 -0.1296 0.0235 1.0000
16.500 1.2338 0.23949 0.23679 -0.1727 0.0324 1.0000
16.750 1.2391 0.24445 0.24178 -0.1762 0.0323 1.0000
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Polar data table (+)
Polar graphs
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