E62 (5.62%) (e62-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 200,000 Max Cl/Cd: 104.15 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e62-il-200000-n5.txt Download as CSV file: xf-e62-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3467 0.12259 0.11905 -0.0269 1.0000 0.0113
-8.750 -0.3461 0.12021 0.11671 -0.0264 1.0000 0.0114
-8.500 -0.3458 0.11790 0.11444 -0.0258 1.0000 0.0114
-8.250 -0.3409 0.11507 0.11164 -0.0265 0.9993 0.0114
-8.000 -0.3266 0.11133 0.10790 -0.0300 0.9968 0.0114
-7.750 -0.3118 0.10764 0.10421 -0.0337 0.9943 0.0114
-7.500 -0.2993 0.10418 0.10077 -0.0366 0.9908 0.0114
-7.250 -0.2911 0.09879 0.09542 -0.0396 0.9871 0.0118
-7.000 -0.2778 0.09426 0.09090 -0.0418 0.9846 0.0122
-6.750 -0.2640 0.09069 0.08733 -0.0439 0.9813 0.0126
-6.500 -0.2514 0.08741 0.08407 -0.0465 0.9757 0.0129
-6.250 -0.2312 0.08359 0.08025 -0.0511 0.9720 0.0134
-6.000 -0.2154 0.08011 0.07678 -0.0546 0.9660 0.0140
-5.750 -0.1947 0.07641 0.07307 -0.0596 0.9610 0.0148
-5.500 -0.1692 0.07269 0.06935 -0.0658 0.9569 0.0182
-5.250 -0.1226 0.06874 0.06534 -0.0807 0.9487 0.0213
-5.000 -0.0863 0.06392 0.06046 -0.0892 0.9461 0.0214
-4.500 -0.0263 0.05343 0.04982 -0.1026 0.9355 0.0219
-4.250 0.0082 0.04825 0.04456 -0.1095 0.9334 0.0226
-4.000 0.0434 0.04370 0.03988 -0.1156 0.9270 0.0226
-3.750 0.0745 0.04047 0.03656 -0.1192 0.9239 0.0179
-3.500 0.1336 0.03349 0.02925 -0.1304 0.9226 0.0143
-3.250 0.1953 0.02640 0.02154 -0.1395 0.9221 0.0118
-3.000 0.2397 0.02348 0.01817 -0.1439 0.9209 0.0114
-2.750 0.2865 0.01980 0.01383 -0.1489 0.9203 0.0113
-2.500 0.3198 0.01782 0.01136 -0.1503 0.9150 0.0114
-2.250 0.3593 0.01537 0.00840 -0.1529 0.9132 0.0124
-2.000 0.3946 0.01446 0.00731 -0.1545 0.9106 0.0165
-1.750 0.4310 0.01363 0.00633 -0.1561 0.9086 0.0206
-1.500 0.4660 0.01280 0.00540 -0.1576 0.9052 0.0263
-1.250 0.4975 0.01234 0.00491 -0.1584 0.8998 0.0472
-1.000 0.5337 0.01177 0.00455 -0.1603 0.8967 0.1235
-0.750 0.5714 0.01126 0.00435 -0.1626 0.8943 0.2407
-0.500 0.6008 0.01094 0.00431 -0.1631 0.8872 0.3544
-0.250 0.6366 0.01033 0.00424 -0.1650 0.8833 0.5640
0.000 0.6567 0.00948 0.00406 -0.1626 0.8763 1.0000
0.250 0.6915 0.00941 0.00384 -0.1639 0.8700 1.0000
0.500 0.7244 0.00937 0.00370 -0.1648 0.8618 1.0000
0.750 0.7609 0.00929 0.00352 -0.1665 0.8546 1.0000
1.000 0.7920 0.00930 0.00346 -0.1671 0.8444 1.0000
1.250 0.8240 0.00931 0.00342 -0.1678 0.8339 1.0000
1.500 0.8559 0.00933 0.00338 -0.1685 0.8227 1.0000
1.750 0.8869 0.00937 0.00337 -0.1690 0.8108 1.0000
2.000 0.9166 0.00945 0.00340 -0.1693 0.7974 1.0000
2.250 0.9452 0.00954 0.00345 -0.1693 0.7826 1.0000
2.500 0.9731 0.00966 0.00359 -0.1692 0.7672 1.0000
2.750 1.0005 0.00980 0.00370 -0.1689 0.7508 1.0000
3.000 1.0274 0.00996 0.00382 -0.1686 0.7325 1.0000
3.250 1.0528 0.01014 0.00398 -0.1679 0.7115 1.0000
3.500 1.0779 0.01035 0.00415 -0.1672 0.6883 1.0000
3.750 1.1021 0.01060 0.00441 -0.1663 0.6609 1.0000
4.000 1.1251 0.01090 0.00463 -0.1651 0.6271 1.0000
4.250 1.1463 0.01129 0.00489 -0.1636 0.5841 1.0000
4.500 1.1653 0.01182 0.00521 -0.1617 0.5303 1.0000
4.750 1.1818 0.01253 0.00563 -0.1594 0.4657 1.0000
5.000 1.1965 0.01343 0.00619 -0.1569 0.3959 1.0000
5.250 1.2117 0.01437 0.00681 -0.1547 0.3287 1.0000
5.500 1.2278 0.01531 0.00755 -0.1527 0.2684 1.0000
5.750 1.2441 0.01630 0.00828 -0.1508 0.2103 1.0000
6.000 1.2607 0.01732 0.00906 -0.1491 0.1578 1.0000
6.250 1.2757 0.01854 0.00994 -0.1471 0.1019 1.0000
6.500 1.2912 0.01972 0.01088 -0.1452 0.0608 1.0000
6.750 1.3076 0.02084 0.01189 -0.1434 0.0351 1.0000
7.000 1.3223 0.02217 0.01314 -0.1412 0.0189 1.0000
7.250 1.3384 0.02335 0.01448 -0.1391 0.0137 1.0000
7.500 1.3513 0.02483 0.01605 -0.1366 0.0098 1.0000
7.750 1.3655 0.02604 0.01745 -0.1342 0.0084 1.0000
8.000 1.3772 0.02749 0.01918 -0.1315 0.0076 1.0000
8.250 1.3881 0.02910 0.02096 -0.1287 0.0069 1.0000
8.500 1.3989 0.03087 0.02290 -0.1260 0.0064 1.0000
8.750 1.4101 0.03281 0.02504 -0.1235 0.0061 1.0000
9.000 1.4217 0.03503 0.02746 -0.1211 0.0058 1.0000
9.250 1.4337 0.03758 0.03027 -0.1189 0.0056 1.0000
9.500 1.4446 0.04054 0.03353 -0.1166 0.0054 1.0000
9.750 1.4526 0.04379 0.03712 -0.1140 0.0053 1.0000
10.000 1.4536 0.04764 0.04137 -0.1108 0.0051 1.0000
10.250 1.4457 0.05225 0.04642 -0.1070 0.0049 1.0000
10.500 1.4362 0.05594 0.05048 -0.1033 0.0047 1.0000
10.750 1.4347 0.05808 0.05291 -0.1006 0.0043 1.0000
11.000 1.4249 0.06187 0.05701 -0.0979 0.0042 1.0000
11.250 1.4148 0.06568 0.06113 -0.0958 0.0040 1.0000
11.500 1.4041 0.06971 0.06543 -0.0944 0.0037 1.0000
11.750 1.3867 0.07507 0.07108 -0.0937 0.0037 1.0000
12.000 1.3684 0.08089 0.07716 -0.0940 0.0038 1.0000
12.250 1.3505 0.08710 0.08362 -0.0953 0.0036 1.0000
12.500 1.3309 0.09422 0.09096 -0.0980 0.0037 1.0000
12.750 1.3102 0.10231 0.09926 -0.1019 0.0037 1.0000
13.000 1.2898 0.11143 0.10856 -0.1074 0.0039 1.0000
13.250 1.2650 0.12287 0.12013 -0.1149 0.0044 1.0000
13.500 1.2477 0.13402 0.13142 -0.1226 0.0045 1.0000
13.750 1.0581 0.14455 0.14245 -0.1177 0.0061 1.0000
14.000 1.0269 0.15936 0.15732 -0.1259 0.0064 1.0000
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Polar data table (+)
Polar graphs
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