EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 100,000 Max Cl/Cd: 47.7 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e361-il-100000.txt Download as CSV file: xf-e361-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4800 0.11714 0.11208 -0.0100 1.0000 0.0960
-10.500 -0.4970 0.11323 0.10827 -0.0155 1.0000 0.0998
-10.250 -0.5319 0.10825 0.10341 -0.0249 1.0000 0.1007
-10.000 -0.4857 0.10471 0.09982 -0.0162 1.0000 0.1040
-9.750 -0.4778 0.10146 0.09658 -0.0163 1.0000 0.1075
-9.500 -0.4851 0.09735 0.09255 -0.0194 1.0000 0.1123
-9.250 -0.5318 0.09121 0.08651 -0.0301 1.0000 0.1147
-9.000 -0.4927 0.08859 0.08392 -0.0232 1.0000 0.1197
-8.750 -0.4931 0.08488 0.08026 -0.0246 1.0000 0.1238
-8.500 -0.5240 0.07968 0.07512 -0.0297 1.0000 0.1276
-8.250 -0.5652 0.07668 0.07205 -0.0302 1.0000 0.1292
-8.000 -0.4354 0.06451 0.06040 -0.0296 1.0000 0.1519
-7.750 -0.4612 0.06036 0.05628 -0.0301 1.0000 0.1563
-7.500 -0.5050 0.05673 0.05256 -0.0291 1.0000 0.1595
-7.250 -0.5568 0.06308 0.05855 -0.0257 1.0000 0.1539
-7.000 -0.5661 0.06016 0.05557 -0.0238 1.0000 0.1647
-6.000 -0.5710 0.03177 0.02600 -0.0119 0.9939 0.0856
-5.750 -0.6014 0.03879 0.03195 -0.0033 1.0000 0.0653
-5.500 -0.5780 0.03552 0.02809 -0.0028 0.9950 0.0592
-5.250 -0.5385 0.03161 0.02358 -0.0050 0.9863 0.0556
-5.000 -0.4970 0.02860 0.01997 -0.0071 0.9774 0.0544
-4.750 -0.4523 0.02633 0.01744 -0.0100 0.9696 0.0563
-4.500 -0.4076 0.02484 0.01563 -0.0128 0.9606 0.0623
-4.250 -0.3652 0.02272 0.01364 -0.0155 0.9524 0.0704
-4.000 -0.3208 0.02096 0.01196 -0.0185 0.9453 0.0882
-3.750 -0.2883 0.01933 0.01066 -0.0196 0.9349 0.1258
-3.500 -0.2741 0.01623 0.00938 -0.0180 0.9245 0.3921
-3.250 -0.2536 0.01603 0.01075 -0.0121 0.9159 0.7964
-3.000 -0.1923 0.01752 0.01199 -0.0137 0.9129 0.8609
-2.750 -0.0733 0.01929 0.01332 -0.0257 0.9168 0.9006
-2.500 0.0221 0.01961 0.01332 -0.0363 0.9149 0.9315
-2.250 0.0845 0.01931 0.01280 -0.0428 0.9051 0.9479
-2.000 0.1378 0.01893 0.01222 -0.0480 0.8942 0.9609
-1.750 0.1828 0.01859 0.01173 -0.0517 0.8815 0.9725
-1.500 0.2272 0.01819 0.01119 -0.0556 0.8688 0.9826
-1.250 0.2707 0.01774 0.01062 -0.0593 0.8568 0.9916
-1.000 0.3121 0.01730 0.01007 -0.0627 0.8461 1.0000
-0.750 0.3309 0.01732 0.01001 -0.0616 0.8341 1.0000
-0.500 0.3498 0.01738 0.01002 -0.0607 0.8226 1.0000
-0.250 0.3688 0.01745 0.01002 -0.0596 0.8128 1.0000
0.000 0.3879 0.01754 0.01006 -0.0586 0.8026 1.0000
0.250 0.4070 0.01766 0.01017 -0.0576 0.7926 1.0000
0.500 0.4262 0.01775 0.01019 -0.0562 0.7840 1.0000
0.750 0.4452 0.01791 0.01037 -0.0553 0.7732 1.0000
1.000 0.4642 0.01804 0.01045 -0.0540 0.7640 1.0000
1.250 0.4830 0.01814 0.01054 -0.0525 0.7536 1.0000
1.500 0.5013 0.01827 0.01067 -0.0511 0.7421 1.0000
1.750 0.5198 0.01831 0.01068 -0.0493 0.7310 1.0000
2.000 0.5383 0.01825 0.01057 -0.0472 0.7190 1.0000
2.250 0.5562 0.01826 0.01058 -0.0454 0.7052 1.0000
2.500 0.5743 0.01826 0.01057 -0.0435 0.6918 1.0000
2.750 0.5929 0.01822 0.01053 -0.0416 0.6786 1.0000
3.000 0.6124 0.01814 0.01042 -0.0397 0.6666 1.0000
3.250 0.6321 0.01805 0.01029 -0.0379 0.6542 1.0000
3.500 0.6507 0.01805 0.01033 -0.0361 0.6403 1.0000
3.750 0.6694 0.01803 0.01035 -0.0343 0.6265 1.0000
4.000 0.6884 0.01797 0.01030 -0.0324 0.6123 1.0000
4.250 0.7075 0.01787 0.01022 -0.0304 0.5973 1.0000
4.500 0.7264 0.01775 0.01011 -0.0284 0.5812 1.0000
4.750 0.7451 0.01760 0.00998 -0.0263 0.5633 1.0000
5.000 0.7638 0.01741 0.00979 -0.0242 0.5438 1.0000
5.250 0.7809 0.01727 0.00967 -0.0219 0.5199 1.0000
5.500 0.7974 0.01711 0.00951 -0.0194 0.4906 1.0000
5.750 0.8119 0.01704 0.00938 -0.0166 0.4499 1.0000
6.000 0.8233 0.01726 0.00937 -0.0133 0.3942 1.0000
6.250 0.8316 0.01799 0.00964 -0.0099 0.3386 1.0000
6.500 0.8407 0.01894 0.01025 -0.0068 0.2984 1.0000
6.750 0.8522 0.01991 0.01096 -0.0042 0.2707 1.0000
7.000 0.8660 0.02086 0.01169 -0.0020 0.2508 1.0000
7.250 0.8817 0.02181 0.01247 -0.0001 0.2345 1.0000
7.500 0.8988 0.02270 0.01331 0.0015 0.2208 1.0000
7.750 0.9166 0.02364 0.01424 0.0031 0.2091 1.0000
8.000 0.9353 0.02465 0.01520 0.0044 0.1989 1.0000
8.250 0.9559 0.02569 0.01613 0.0054 0.1896 1.0000
8.500 0.9737 0.02671 0.01732 0.0069 0.1813 1.0000
8.750 0.9967 0.02800 0.01844 0.0073 0.1733 1.0000
9.000 1.0125 0.02901 0.01972 0.0091 0.1663 1.0000
9.250 1.0365 0.03041 0.02096 0.0093 0.1594 1.0000
9.500 1.0506 0.03162 0.02250 0.0112 0.1534 1.0000
9.750 1.0694 0.03285 0.02378 0.0123 0.1474 1.0000
10.000 1.0877 0.03462 0.02566 0.0132 0.1423 1.0000
10.250 1.1003 0.03601 0.02733 0.0151 0.1369 1.0000
10.500 1.1202 0.03749 0.02880 0.0157 0.1318 1.0000
10.750 1.1303 0.03962 0.03123 0.0176 0.1279 1.0000
11.000 1.1363 0.04143 0.03339 0.0199 0.1238 1.0000
11.250 1.1516 0.04295 0.03496 0.0210 0.1193 1.0000
11.500 1.1653 0.04560 0.03768 0.0218 0.1157 1.0000
11.750 1.1562 0.04790 0.04046 0.0254 0.1135 1.0000
12.000 1.1475 0.05039 0.04330 0.0285 0.1110 1.0000
12.250 1.1413 0.05271 0.04584 0.0312 0.1086 1.0000
12.500 1.1579 0.05441 0.04753 0.0317 0.1050 1.0000
12.750 1.1596 0.05783 0.05101 0.0329 0.1027 1.0000
13.000 1.1325 0.06083 0.05429 0.0364 0.1023 1.0000
13.250 1.1022 0.06462 0.05833 0.0383 0.1020 1.0000
13.500 1.0714 0.06944 0.06337 0.0385 0.1021 1.0000
13.750 1.0387 0.07522 0.06934 0.0374 0.1023 1.0000
14.000 1.0033 0.08232 0.07659 0.0349 0.1027 1.0000
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Polar data table (+)
Polar graphs
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