E61 (5.64%) (e61-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 200,000 Max Cl/Cd: 110.84 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e61-il-200000-n5.txt Download as CSV file: xf-e61-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E61 (5.64%)
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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.1494 0.09164 0.08812 -0.0651 0.9570 0.0135
-6.250 -0.1270 0.08656 0.08308 -0.0702 0.9455 0.0153
-5.750 -0.0874 0.08075 0.07728 -0.0819 0.9318 0.0161
-5.500 -0.0680 0.07725 0.07378 -0.0861 0.9262 0.0162
-5.250 -0.0397 0.07299 0.06949 -0.0925 0.9234 0.0162
-5.000 -0.0212 0.06955 0.06605 -0.0961 0.9167 0.0162
-4.750 -0.0051 0.06414 0.06066 -0.0995 0.9127 0.0170
-4.500 0.0198 0.06056 0.05705 -0.1031 0.9105 0.0178
-4.250 0.0424 0.05744 0.05392 -0.1067 0.9047 0.0187
-4.000 0.0772 0.05360 0.05002 -0.1136 0.9007 0.0198
-3.750 0.1245 0.04904 0.04534 -0.1237 0.8987 0.0220
-2.750 0.3801 0.02692 0.02208 -0.1731 0.8969 0.0225
-2.500 0.4418 0.02247 0.01702 -0.1820 0.8970 0.0216
-2.250 0.4897 0.02035 0.01437 -0.1866 0.8964 0.0249
-2.000 0.5293 0.01850 0.01209 -0.1897 0.8932 0.0242
-1.750 0.5669 0.01713 0.01034 -0.1919 0.8901 0.0234
-1.500 0.6046 0.01603 0.00898 -0.1940 0.8878 0.0229
-1.250 0.6423 0.01512 0.00790 -0.1960 0.8858 0.0225
-1.000 0.6807 0.01434 0.00703 -0.1982 0.8841 0.0224
-0.750 0.7148 0.01386 0.00645 -0.1996 0.8802 0.0227
-0.500 0.7472 0.01352 0.00602 -0.2005 0.8751 0.0234
-0.250 0.7843 0.01312 0.00552 -0.2024 0.8720 0.0251
0.000 0.8244 0.01270 0.00509 -0.2049 0.8696 0.0355
0.250 0.8580 0.01207 0.00525 -0.2067 0.8627 0.3091
0.500 0.8985 0.01150 0.00518 -0.2096 0.8585 0.5384
1.000 0.9560 0.01062 0.00483 -0.2093 0.8445 1.0000
1.250 0.9878 0.01063 0.00478 -0.2101 0.8358 1.0000
1.500 1.0244 0.01056 0.00463 -0.2118 0.8280 1.0000
1.750 1.0562 0.01057 0.00459 -0.2126 0.8177 1.0000
2.000 1.0869 0.01062 0.00460 -0.2131 0.8065 1.0000
2.250 1.1175 0.01068 0.00466 -0.2135 0.7946 1.0000
2.500 1.1474 0.01076 0.00471 -0.2139 0.7817 1.0000
2.750 1.1764 0.01087 0.00479 -0.2140 0.7677 1.0000
3.000 1.2045 0.01100 0.00490 -0.2139 0.7527 1.0000
3.250 1.2319 0.01116 0.00503 -0.2137 0.7361 1.0000
3.500 1.2575 0.01135 0.00526 -0.2131 0.7173 1.0000
3.750 1.2824 0.01157 0.00546 -0.2124 0.6961 1.0000
4.000 1.3063 0.01183 0.00568 -0.2114 0.6721 1.0000
4.250 1.3288 0.01214 0.00593 -0.2101 0.6426 1.0000
4.500 1.3494 0.01253 0.00622 -0.2085 0.6061 1.0000
4.750 1.3677 0.01305 0.00657 -0.2064 0.5621 1.0000
5.000 1.3833 0.01371 0.00708 -0.2038 0.5125 1.0000
5.250 1.3929 0.01471 0.00771 -0.2002 0.4429 1.0000
5.500 1.3967 0.01614 0.00857 -0.1956 0.3512 1.0000
5.750 1.3979 0.01788 0.00961 -0.1910 0.2463 1.0000
6.000 1.4034 0.01954 0.01067 -0.1873 0.1587 1.0000
6.500 1.4274 0.02202 0.01264 -0.1821 0.0665 1.0000
6.750 1.4346 0.02376 0.01404 -0.1788 0.0188 1.0000
7.000 1.4481 0.02493 0.01524 -0.1762 0.0107 1.0000
7.250 1.4620 0.02608 0.01649 -0.1738 0.0083 1.0000
7.500 1.4761 0.02717 0.01782 -0.1715 0.0069 1.0000
7.750 1.4893 0.02838 0.01920 -0.1691 0.0061 1.0000
8.000 1.5011 0.02974 0.02075 -0.1665 0.0057 1.0000
8.250 1.5106 0.03131 0.02252 -0.1636 0.0053 1.0000
8.500 1.5183 0.03308 0.02448 -0.1606 0.0051 1.0000
8.750 1.5242 0.03509 0.02668 -0.1574 0.0049 1.0000
9.000 1.5302 0.03718 0.02895 -0.1544 0.0048 1.0000
9.250 1.5353 0.03959 0.03155 -0.1513 0.0047 1.0000
9.500 1.5417 0.04209 0.03425 -0.1486 0.0046 1.0000
9.750 1.5495 0.04476 0.03713 -0.1461 0.0046 1.0000
10.000 1.5582 0.04758 0.04019 -0.1438 0.0045 1.0000
10.250 1.5664 0.05069 0.04357 -0.1416 0.0045 1.0000
10.500 1.5729 0.05373 0.04696 -0.1393 0.0045 1.0000
10.750 1.5758 0.05727 0.05082 -0.1368 0.0045 1.0000
11.000 1.5752 0.06092 0.05479 -0.1343 0.0045 1.0000
11.250 1.5722 0.06466 0.05884 -0.1319 0.0045 1.0000
11.500 1.5663 0.06866 0.06315 -0.1297 0.0046 1.0000
11.750 1.5581 0.07294 0.06773 -0.1278 0.0046 1.0000
12.000 1.5464 0.07782 0.07292 -0.1262 0.0046 1.0000
12.250 1.5347 0.08270 0.07809 -0.1253 0.0046 1.0000
12.500 1.5207 0.08809 0.08376 -0.1249 0.0046 1.0000
12.750 1.5067 0.09371 0.08965 -0.1253 0.0047 1.0000
13.000 1.4906 0.10003 0.09624 -0.1266 0.0047 1.0000
13.250 1.4750 0.10667 0.10312 -0.1287 0.0047 1.0000
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Polar data table (+)
Polar graphs
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