EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 50,000 Max Cl/Cd: 11.63 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e562-il-50000.txt Download as CSV file: xf-e562-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3192 0.11771 0.11074 -0.0295 1.0000 0.2748
-9.250 -0.3622 0.10457 0.09773 -0.0386 1.0000 0.1804
-9.000 -0.3646 0.10012 0.09334 -0.0386 1.0000 0.1749
-8.750 -0.3944 0.09374 0.08713 -0.0409 1.0000 0.1640
-8.500 -0.5120 0.07709 0.07097 -0.0501 1.0000 0.1384
-8.250 -0.5383 0.07094 0.06489 -0.0523 1.0000 0.1367
-8.000 -0.5652 0.06459 0.05856 -0.0547 1.0000 0.1348
-7.750 -0.5910 0.05733 0.05111 -0.0583 1.0000 0.1333
-7.500 -0.6027 0.05030 0.04360 -0.0623 1.0000 0.1345
-7.250 -0.5976 0.04443 0.03707 -0.0658 1.0000 0.1391
-7.000 -0.5825 0.04296 0.03569 -0.0645 1.0000 0.1472
-6.750 -0.5663 0.04037 0.03291 -0.0650 1.0000 0.1587
-6.500 -0.5484 0.03851 0.03095 -0.0649 1.0000 0.1742
-6.250 -0.5282 0.03665 0.02888 -0.0655 1.0000 0.1985
-6.000 -0.5138 0.03733 0.02994 -0.0626 1.0000 0.2225
-5.750 -0.4993 0.03807 0.03087 -0.0598 1.0000 0.2501
-5.500 -0.4851 0.03890 0.03179 -0.0572 1.0000 0.2783
-5.250 -0.4753 0.04064 0.03373 -0.0524 1.0000 0.2990
-5.000 -0.4591 0.04059 0.03357 -0.0512 1.0000 0.3252
-4.750 -0.4485 0.04155 0.03460 -0.0475 1.0000 0.3431
-4.500 -0.4368 0.04211 0.03518 -0.0445 1.0000 0.3612
-4.250 -0.4239 0.04231 0.03534 -0.0423 1.0000 0.3794
-4.000 -0.4102 0.04231 0.03528 -0.0405 1.0000 0.3975
-3.750 -0.3949 0.04204 0.03491 -0.0396 1.0000 0.4150
-3.500 -0.3793 0.04176 0.03453 -0.0388 1.0000 0.4318
-3.250 -0.3629 0.04143 0.03410 -0.0383 1.0000 0.4477
-3.000 -0.3177 0.04119 0.03355 -0.0438 0.9908 0.4726
-2.750 -0.2775 0.04161 0.03386 -0.0465 0.9778 0.4916
-2.500 -0.2382 0.04176 0.03388 -0.0493 0.9648 0.5105
-2.250 -0.1993 0.04171 0.03368 -0.0523 0.9519 0.5288
-2.000 -0.1612 0.04155 0.03337 -0.0554 0.9393 0.5460
-1.750 -0.1234 0.04138 0.03305 -0.0584 0.9265 0.5627
-1.500 -0.0853 0.04122 0.03277 -0.0614 0.9141 0.5788
-1.250 -0.0453 0.04113 0.03254 -0.0645 0.9022 0.5955
-1.000 -0.0068 0.04102 0.03232 -0.0673 0.8900 0.6117
-0.750 0.0225 0.04098 0.03220 -0.0687 0.8772 0.6269
-0.500 0.0538 0.04099 0.03212 -0.0703 0.8647 0.6424
-0.250 0.0885 0.04103 0.03209 -0.0722 0.8535 0.6590
0.000 0.1259 0.04101 0.03201 -0.0742 0.8423 0.6763
0.250 0.1488 0.04122 0.03218 -0.0744 0.8295 0.6921
0.500 0.1752 0.04145 0.03239 -0.0750 0.8180 0.7088
0.750 0.2178 0.04135 0.03223 -0.0772 0.8086 0.7294
1.000 0.2344 0.04181 0.03268 -0.0765 0.7959 0.7460
1.250 0.2546 0.04227 0.03314 -0.0762 0.7846 0.7648
1.500 0.2932 0.04215 0.03300 -0.0774 0.7756 0.7890
1.750 0.3043 0.04277 0.03367 -0.0758 0.7636 0.8092
2.000 0.3196 0.04336 0.03430 -0.0748 0.7528 0.8344
2.250 0.3508 0.04308 0.03408 -0.0744 0.7445 0.8686
2.500 0.3525 0.04396 0.03510 -0.0720 0.7329 0.9070
2.750 0.3948 0.04460 0.03579 -0.0770 0.7214 1.0000
3.000 0.4685 0.04484 0.03585 -0.0863 0.7117 1.0000
3.250 0.4887 0.04685 0.03774 -0.0893 0.6993 1.0000
3.500 0.5190 0.04835 0.03910 -0.0922 0.6886 1.0000
3.750 0.5673 0.04881 0.03944 -0.0957 0.6798 1.0000
4.000 0.5691 0.05136 0.04191 -0.0952 0.6683 1.0000
4.250 0.6012 0.05243 0.04290 -0.0966 0.6592 1.0000
4.500 0.6153 0.05438 0.04482 -0.0967 0.6494 1.0000
4.750 0.6236 0.05668 0.04708 -0.0964 0.6397 1.0000
5.000 0.6614 0.05735 0.04772 -0.0976 0.6310 1.0000
5.250 0.6500 0.06087 0.05122 -0.0963 0.6214 1.0000
5.500 0.7045 0.06057 0.05094 -0.0980 0.6132 1.0000
5.750 0.6740 0.06534 0.05570 -0.0961 0.6039 1.0000
6.000 0.7101 0.06622 0.05659 -0.0968 0.5954 1.0000
6.250 0.6948 0.07019 0.06058 -0.0958 0.5872 1.0000
6.500 0.7253 0.07151 0.06191 -0.0963 0.5788 1.0000
6.750 0.7103 0.07562 0.06605 -0.0957 0.5717 1.0000
7.000 0.7425 0.07688 0.06736 -0.0961 0.5627 1.0000
7.250 0.7240 0.08147 0.07198 -0.0957 0.5577 1.0000
7.500 0.7645 0.08222 0.07279 -0.0961 0.5474 1.0000
7.750 0.7416 0.08728 0.07788 -0.0960 0.5438 1.0000
8.000 0.7356 0.09138 0.08203 -0.0964 0.5410 1.0000
8.250 0.7360 0.09518 0.08589 -0.0970 0.5385 1.0000
8.500 0.7574 0.09758 0.08836 -0.0973 0.5294 1.0000
8.750 0.7579 0.10190 0.09274 -0.0983 0.5301 1.0000
9.000 0.7698 0.10612 0.09705 -0.0997 0.5318 1.0000
9.250 0.6828 0.11591 0.10690 -0.1034 0.6028 1.0000
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Polar data table (+)
Polar graphs
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