EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 100,000 Max Cl/Cd: 45.65 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e560-il-100000.txt Download as CSV file: xf-e560-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 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 -0.5980 0.06520 0.06015 -0.0747 1.0000 0.0669
-10.500 -0.6339 0.06105 0.05602 -0.0742 1.0000 0.0665
-10.250 -0.6682 0.05790 0.05288 -0.0729 1.0000 0.0659
-10.000 -0.6989 0.05326 0.04813 -0.0753 1.0000 0.0655
-9.750 -0.7184 0.04898 0.04355 -0.0772 1.0000 0.0656
-9.500 -0.7257 0.04504 0.03919 -0.0791 1.0000 0.0664
-9.250 -0.7211 0.04204 0.03599 -0.0796 1.0000 0.0679
-9.000 -0.7102 0.04054 0.03454 -0.0789 1.0000 0.0699
-8.750 -0.6981 0.03863 0.03248 -0.0792 1.0000 0.0723
-8.500 -0.6835 0.03638 0.02992 -0.0800 1.0000 0.0751
-8.250 -0.6496 0.03410 0.02750 -0.0835 0.9956 0.0802
-8.000 -0.6065 0.03219 0.02536 -0.0885 0.9885 0.0901
-7.750 -0.5626 0.03102 0.02433 -0.0933 0.9816 0.1068
-7.500 -0.5188 0.02990 0.02314 -0.0980 0.9736 0.1308
-7.250 -0.4781 0.02983 0.02314 -0.1013 0.9646 0.1507
-7.000 -0.4354 0.02978 0.02289 -0.1051 0.9560 0.1711
-6.750 -0.3917 0.03054 0.02382 -0.1081 0.9479 0.1901
-6.500 -0.3562 0.03088 0.02418 -0.1095 0.9375 0.2055
-6.250 -0.3160 0.03057 0.02374 -0.1122 0.9289 0.2200
-6.000 -0.2745 0.03050 0.02367 -0.1145 0.9210 0.2331
-5.750 -0.2410 0.03052 0.02377 -0.1152 0.9109 0.2432
-5.500 -0.1949 0.03004 0.02318 -0.1185 0.9048 0.2568
-5.250 -0.1613 0.02948 0.02244 -0.1200 0.8942 0.2696
-5.000 -0.1127 0.02888 0.02164 -0.1237 0.8889 0.2842
-4.750 -0.0838 0.02897 0.02191 -0.1232 0.8780 0.2918
-4.500 -0.0353 0.02817 0.02096 -0.1267 0.8731 0.3053
-4.250 0.0005 0.02752 0.02008 -0.1285 0.8632 0.3181
-4.000 0.0451 0.02710 0.01976 -0.1305 0.8579 0.3280
-3.750 0.1007 0.02617 0.01871 -0.1352 0.8549 0.3412
-3.500 0.1328 0.02562 0.01795 -0.1363 0.8431 0.3530
-3.250 0.1853 0.02494 0.01727 -0.1401 0.8389 0.3645
-3.000 0.2163 0.02452 0.01677 -0.1406 0.8271 0.3742
-2.750 0.2700 0.02364 0.01569 -0.1451 0.8218 0.3880
-2.500 0.2979 0.02346 0.01555 -0.1447 0.8092 0.3962
-2.250 0.3356 0.02298 0.01493 -0.1465 0.7991 0.4076
-2.000 0.3765 0.02253 0.01435 -0.1486 0.7897 0.4193
-1.750 0.4046 0.02235 0.01416 -0.1484 0.7774 0.4280
-1.500 0.4412 0.02202 0.01367 -0.1499 0.7673 0.4402
-1.250 0.4730 0.02183 0.01345 -0.1503 0.7564 0.4496
-1.000 0.5004 0.02173 0.01329 -0.1502 0.7444 0.4600
-0.750 0.5344 0.02157 0.01300 -0.1511 0.7345 0.4720
-0.500 0.5620 0.02149 0.01292 -0.1508 0.7234 0.4814
-0.250 0.5891 0.02150 0.01286 -0.1507 0.7123 0.4930
0.000 0.6239 0.02136 0.01262 -0.1516 0.7037 0.5055
0.250 0.6457 0.02146 0.01277 -0.1505 0.6919 0.5153
0.500 0.6751 0.02148 0.01272 -0.1506 0.6826 0.5281
0.750 0.7033 0.02152 0.01272 -0.1506 0.6728 0.5415
1.000 0.7278 0.02164 0.01289 -0.1499 0.6631 0.5531
1.250 0.7579 0.02163 0.01284 -0.1500 0.6547 0.5671
1.500 0.7808 0.02185 0.01311 -0.1492 0.6450 0.5812
1.750 0.8116 0.02186 0.01307 -0.1495 0.6373 0.5973
2.000 0.8334 0.02213 0.01342 -0.1484 0.6278 0.6132
2.250 0.8635 0.02216 0.01344 -0.1485 0.6205 0.6316
2.500 0.8841 0.02247 0.01387 -0.1472 0.6116 0.6500
2.750 0.9123 0.02254 0.01397 -0.1470 0.6045 0.6725
3.000 0.9340 0.02284 0.01438 -0.1459 0.5964 0.6973
3.250 0.9586 0.02296 0.01458 -0.1450 0.5891 0.7266
3.500 0.9814 0.02314 0.01487 -0.1438 0.5825 0.7634
3.750 0.9953 0.02332 0.01528 -0.1409 0.5749 0.8102
4.000 1.0111 0.02293 0.01505 -0.1375 0.5697 0.9318
4.250 1.0418 0.02360 0.01568 -0.1393 0.5610 1.0000
4.500 1.0755 0.02397 0.01591 -0.1407 0.5546 1.0000
4.750 1.1008 0.02460 0.01651 -0.1406 0.5477 1.0000
5.000 1.1254 0.02515 0.01704 -0.1402 0.5404 1.0000
5.250 1.1610 0.02543 0.01717 -0.1415 0.5353 1.0000
5.500 1.1739 0.02638 0.01827 -0.1395 0.5273 1.0000
5.750 1.2037 0.02675 0.01858 -0.1398 0.5213 1.0000
6.000 1.2273 0.02743 0.01929 -0.1393 0.5152 1.0000
6.250 1.2460 0.02820 0.02014 -0.1380 0.5081 1.0000
6.500 1.2803 0.02844 0.02028 -0.1389 0.5028 1.0000
6.750 1.2923 0.02952 0.02151 -0.1368 0.4957 1.0000
7.000 1.3169 0.03005 0.02207 -0.1363 0.4894 1.0000
7.250 1.3505 0.03038 0.02233 -0.1371 0.4843 1.0000
7.500 1.3560 0.03164 0.02380 -0.1340 0.4766 1.0000
7.750 1.3873 0.03191 0.02405 -0.1345 0.4709 1.0000
8.000 1.4033 0.03287 0.02511 -0.1328 0.4645 1.0000
8.250 1.4193 0.03369 0.02603 -0.1312 0.4576 1.0000
8.500 1.4613 0.03357 0.02580 -0.1331 0.4523 1.0000
8.750 1.4566 0.03523 0.02774 -0.1286 0.4446 1.0000
9.000 1.4874 0.03536 0.02786 -0.1289 0.4383 1.0000
9.250 1.5027 0.03627 0.02886 -0.1272 0.4317 1.0000
9.500 1.5148 0.03711 0.02984 -0.1249 0.4244 1.0000
9.750 1.5584 0.03675 0.02937 -0.1268 0.4182 1.0000
10.000 1.5460 0.03855 0.03146 -0.1215 0.4104 1.0000
10.250 1.5949 0.03776 0.03054 -0.1239 0.4035 1.0000
10.500 1.5809 0.03962 0.03267 -0.1184 0.3961 1.0000
10.750 1.6186 0.03913 0.03214 -0.1193 0.3885 1.0000
11.000 1.6160 0.04047 0.03365 -0.1152 0.3813 1.0000
11.250 1.6396 0.04044 0.03365 -0.1143 0.3733 1.0000
11.500 1.6452 0.04123 0.03453 -0.1111 0.3660 1.0000
11.750 1.6532 0.04173 0.03512 -0.1082 0.3581 1.0000
12.000 1.6661 0.04215 0.03559 -0.1061 0.3503 1.0000
12.250 1.6664 0.04296 0.03650 -0.1025 0.3423 1.0000
12.500 1.6774 0.04343 0.03701 -0.1002 0.3341 1.0000
12.750 1.6788 0.04422 0.03789 -0.0970 0.3258 1.0000
13.000 1.6797 0.04530 0.03905 -0.0941 0.3177 1.0000
13.250 1.6989 0.04513 0.03886 -0.0927 0.3081 1.0000
13.500 1.6742 0.04798 0.04193 -0.0883 0.3010 1.0000
13.750 1.7046 0.04712 0.04093 -0.0878 0.2903 1.0000
14.000 1.6633 0.05160 0.04572 -0.0834 0.2838 1.0000
14.250 1.6812 0.05163 0.04568 -0.0822 0.2734 1.0000
14.500 1.6557 0.05551 0.04975 -0.0797 0.2655 1.0000
14.750 1.6541 0.05751 0.05178 -0.0783 0.2561 1.0000
15.000 1.6697 0.05783 0.05198 -0.0772 0.2448 1.0000
15.250 1.6300 0.06412 0.05856 -0.0761 0.2378 1.0000
15.500 1.6347 0.06580 0.06019 -0.0753 0.2274 1.0000
15.750 1.6242 0.06936 0.06381 -0.0748 0.2179 1.0000
16.000 1.6056 0.07429 0.06885 -0.0749 0.2093 1.0000
16.250 1.6110 0.07617 0.07065 -0.0745 0.1988 1.0000
16.500 1.5911 0.08165 0.07627 -0.0752 0.1904 1.0000
16.750 1.5832 0.08567 0.08032 -0.0756 0.1816 1.0000
17.000 1.5912 0.08736 0.08185 -0.0753 0.1710 1.0000
17.250 1.5637 0.09461 0.08935 -0.0774 0.1645 1.0000
17.500 1.5649 0.09742 0.09207 -0.0777 0.1552 1.0000
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Polar data table (+)
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