E61 (5.64%) (e61-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 100,000 Max Cl/Cd: 75.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e61-il-100000-n5.txt Download as CSV file: xf-e61-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3245 0.12656 0.12184 -0.0238 1.0000 0.0197
-8.500 -0.3247 0.12457 0.11989 -0.0230 1.0000 0.0202
-8.250 -0.3256 0.12263 0.11800 -0.0222 1.0000 0.0219
-8.000 -0.3167 0.11990 0.11524 -0.0241 0.9980 0.0228
-7.750 -0.3024 0.11730 0.11265 -0.0284 0.9945 0.0244
-7.500 -0.2916 0.11547 0.11084 -0.0324 0.9898 0.0251
-7.250 -0.2815 0.11404 0.10943 -0.0370 0.9846 0.0254
-7.000 -0.2759 0.11275 0.10818 -0.0406 0.9777 0.0256
-6.750 -0.2578 0.10969 0.10513 -0.0463 0.9726 0.0257
-6.500 -0.2476 0.10273 0.09819 -0.0436 0.9718 0.0268
-6.250 -0.2377 0.09919 0.09466 -0.0435 0.9672 0.0278
-6.000 -0.2242 0.09591 0.09140 -0.0456 0.9623 0.0296
-5.750 -0.2089 0.09277 0.08826 -0.0489 0.9572 0.0312
-5.500 -0.1945 0.08972 0.08522 -0.0521 0.9507 0.0329
-5.250 -0.1726 0.08659 0.08209 -0.0585 0.9444 0.0356
-5.000 -0.1315 0.08365 0.07910 -0.0732 0.9370 0.0371
-4.750 -0.0972 0.07998 0.07537 -0.0827 0.9311 0.0374
-4.500 -0.0968 0.07508 0.07055 -0.0788 0.9267 0.0385
-4.250 -0.0814 0.07160 0.06706 -0.0786 0.9237 0.0406
-4.000 -0.0601 0.06849 0.06393 -0.0820 0.9179 0.0439
-3.500 0.0221 0.05990 0.05515 -0.1003 0.9107 0.0547
-3.250 0.0594 0.05623 0.05139 -0.1069 0.9067 0.0586
-3.000 0.1438 0.05010 0.04490 -0.1273 0.9045 0.0654
-2.750 0.1758 0.04659 0.04135 -0.1308 0.9013 0.0671
-2.500 0.2587 0.03901 0.03324 -0.1461 0.9020 0.0349
-2.250 0.3314 0.03422 0.02777 -0.1579 0.9023 0.0367
-2.000 0.3879 0.03069 0.02373 -0.1657 0.9019 0.0358
-1.750 0.4400 0.02801 0.02050 -0.1717 0.9011 0.0344
-1.500 0.4870 0.02607 0.01797 -0.1760 0.8998 0.0334
-1.250 0.5300 0.02461 0.01608 -0.1792 0.8982 0.0329
-1.000 0.5709 0.02346 0.01463 -0.1818 0.8966 0.0329
-0.750 0.5998 0.02289 0.01392 -0.1821 0.8907 0.0333
-0.500 0.6354 0.02228 0.01318 -0.1838 0.8872 0.0344
-0.250 0.6737 0.02175 0.01247 -0.1858 0.8846 0.0369
0.000 0.7083 0.02139 0.01206 -0.1872 0.8805 0.0479
0.250 0.7418 0.02085 0.01189 -0.1887 0.8753 0.1674
0.500 0.7678 0.01914 0.01186 -0.1882 0.8719 1.0000
0.750 0.8001 0.01913 0.01161 -0.1889 0.8671 1.0000
1.000 0.8290 0.01919 0.01151 -0.1890 0.8605 1.0000
1.250 0.8656 0.01898 0.01116 -0.1905 0.8572 1.0000
1.500 0.8916 0.01911 0.01121 -0.1901 0.8489 1.0000
1.750 0.9274 0.01890 0.01095 -0.1914 0.8446 1.0000
2.000 0.9556 0.01894 0.01095 -0.1913 0.8368 1.0000
2.250 0.9912 0.01871 0.01069 -0.1926 0.8314 1.0000
2.500 1.0202 0.01870 0.01069 -0.1926 0.8229 1.0000
2.750 1.0582 0.01838 0.01044 -0.1942 0.8169 1.0000
3.000 1.0864 0.01838 0.01049 -0.1940 0.8067 1.0000
3.250 1.1193 0.01823 0.01039 -0.1947 0.7972 1.0000
3.500 1.1581 0.01792 0.01014 -0.1964 0.7880 1.0000
3.750 1.1905 0.01782 0.01011 -0.1969 0.7756 1.0000
4.000 1.2228 0.01772 0.01018 -0.1974 0.7617 1.0000
4.250 1.2511 0.01774 0.01030 -0.1971 0.7452 1.0000
4.500 1.2797 0.01776 0.01042 -0.1968 0.7262 1.0000
4.750 1.3102 0.01775 0.01049 -0.1969 0.7049 1.0000
5.000 1.3380 0.01783 0.01065 -0.1964 0.6796 1.0000
5.250 1.3620 0.01803 0.01100 -0.1952 0.6485 1.0000
5.500 1.3861 0.01829 0.01126 -0.1939 0.6093 1.0000
5.750 1.4076 0.01871 0.01160 -0.1922 0.5603 1.0000
6.000 1.4258 0.01938 0.01208 -0.1899 0.5032 1.0000
6.250 1.4396 0.02031 0.01278 -0.1870 0.4439 1.0000
6.500 1.4428 0.02184 0.01375 -0.1824 0.3564 1.0000
6.750 1.4395 0.02386 0.01500 -0.1771 0.2560 1.0000
7.000 1.4419 0.02582 0.01637 -0.1732 0.1738 1.0000
7.250 1.4457 0.02789 0.01789 -0.1697 0.1003 1.0000
7.500 1.4489 0.03019 0.01968 -0.1661 0.0403 1.0000
7.750 1.4555 0.03222 0.02174 -0.1627 0.0218 1.0000
8.000 1.4650 0.03394 0.02366 -0.1597 0.0172 1.0000
8.250 1.4715 0.03597 0.02587 -0.1564 0.0150 1.0000
8.500 1.4772 0.03804 0.02819 -0.1531 0.0139 1.0000
8.750 1.4829 0.04012 0.03054 -0.1500 0.0132 1.0000
9.000 1.4885 0.04228 0.03294 -0.1470 0.0124 1.0000
9.250 1.4950 0.04440 0.03526 -0.1444 0.0111 1.0000
9.500 1.5007 0.04663 0.03766 -0.1419 0.0100 1.0000
9.750 1.5029 0.04950 0.04070 -0.1393 0.0092 1.0000
10.000 1.5073 0.05253 0.04393 -0.1368 0.0088 1.0000
10.250 1.5149 0.05551 0.04718 -0.1346 0.0087 1.0000
10.500 1.5229 0.05869 0.05066 -0.1326 0.0086 1.0000
10.750 1.5294 0.06222 0.05453 -0.1305 0.0084 1.0000
11.000 1.5325 0.06601 0.05877 -0.1284 0.0084 1.0000
11.250 1.5314 0.07008 0.06322 -0.1263 0.0084 1.0000
11.500 1.5264 0.07445 0.06796 -0.1244 0.0083 1.0000
11.750 1.5181 0.07910 0.07296 -0.1227 0.0084 1.0000
12.000 1.5064 0.08418 0.07840 -0.1215 0.0083 1.0000
12.250 1.4933 0.08947 0.08402 -0.1209 0.0084 1.0000
12.500 1.4787 0.09507 0.08993 -0.1210 0.0084 1.0000
12.750 1.4630 0.10105 0.09620 -0.1219 0.0084 1.0000
13.000 1.4463 0.10753 0.10297 -0.1237 0.0084 1.0000
13.250 1.4301 0.11439 0.11008 -0.1265 0.0084 1.0000
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Polar data table (+)
Polar graphs
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