EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 50,000 Max Cl/Cd: 24.18 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1211-il-50000-n5.txt Download as CSV file: xf-e1211-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1211 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2717 0.11139 0.10378 -0.0392 1.0000 0.1250
-10.750 -0.2678 0.10891 0.10136 -0.0393 1.0000 0.1291
-10.500 -0.2854 0.10397 0.09648 -0.0418 1.0000 0.1329
-10.250 -0.2710 0.10287 0.09545 -0.0405 1.0000 0.1361
-10.000 -0.2692 0.10046 0.09311 -0.0405 1.0000 0.1399
-9.750 -0.2840 0.09631 0.08905 -0.0419 1.0000 0.1432
-9.500 -0.2880 0.09366 0.08651 -0.0419 1.0000 0.1463
-9.250 -0.2826 0.09238 0.08534 -0.0405 1.0000 0.1494
-9.000 -0.2939 0.08999 0.08309 -0.0398 1.0000 0.1521
-8.750 -0.3163 0.08523 0.07845 -0.0430 0.9913 0.1559
-8.500 -0.2897 0.08218 0.07538 -0.0474 0.9676 0.1602
-8.000 -0.2878 0.06969 0.06276 -0.0636 0.9177 0.1715
-7.750 -0.2426 0.06912 0.06212 -0.0652 0.9014 0.1760
-7.500 -0.2830 0.05565 0.04824 -0.0816 0.8771 0.1855
-7.250 -0.2349 0.05661 0.04921 -0.0812 0.8612 0.1888
-7.000 -0.2176 0.05366 0.04608 -0.0842 0.8428 0.1942
-6.750 -0.2278 0.04711 0.03900 -0.0898 0.8244 0.2021
-6.500 -0.1963 0.04686 0.03871 -0.0895 0.8085 0.2056
-6.250 -0.1743 0.04510 0.03672 -0.0906 0.7940 0.2111
-6.000 -0.1692 0.04122 0.03227 -0.0928 0.7780 0.2184
-5.750 -0.1434 0.04090 0.03195 -0.0919 0.7632 0.2218
-5.500 -0.1176 0.04006 0.03094 -0.0918 0.7506 0.2265
-5.250 -0.1003 0.03844 0.02902 -0.0920 0.7360 0.2323
-5.000 -0.0792 0.03694 0.02719 -0.0924 0.7234 0.2379
-4.750 -0.0544 0.03643 0.02661 -0.0917 0.7109 0.2419
-4.500 -0.0318 0.03573 0.02577 -0.0912 0.6983 0.2469
-4.250 -0.0067 0.03451 0.02414 -0.0917 0.6874 0.2535
-4.000 0.0161 0.03384 0.02336 -0.0913 0.6749 0.2579
-3.750 0.0434 0.03338 0.02280 -0.0909 0.6650 0.2626
-3.500 0.0663 0.03290 0.02218 -0.0905 0.6528 0.2682
-3.250 0.0941 0.03208 0.02097 -0.0908 0.6435 0.2746
-3.000 0.1172 0.03177 0.02068 -0.0901 0.6318 0.2790
-2.750 0.1447 0.03140 0.02021 -0.0898 0.6228 0.2844
-2.500 0.1687 0.03109 0.01978 -0.0893 0.6119 0.2903
-2.250 0.1964 0.03062 0.01902 -0.0893 0.6028 0.2968
-2.000 0.2207 0.03047 0.01891 -0.0886 0.5931 0.3017
-1.750 0.2466 0.03026 0.01862 -0.0882 0.5839 0.3080
-1.500 0.2737 0.03001 0.01816 -0.0880 0.5755 0.3149
-1.250 0.2980 0.02991 0.01805 -0.0874 0.5657 0.3209
-1.000 0.3265 0.02970 0.01774 -0.0871 0.5587 0.3281
-0.750 0.3492 0.02978 0.01777 -0.0865 0.5489 0.3357
-0.500 0.3758 0.02965 0.01757 -0.0860 0.5411 0.3429
-0.250 0.4011 0.02966 0.01754 -0.0854 0.5335 0.3511
0.000 0.4255 0.02979 0.01759 -0.0849 0.5248 0.3610
0.250 0.4534 0.02968 0.01745 -0.0845 0.5183 0.3701
0.500 0.4764 0.02993 0.01768 -0.0839 0.5100 0.3810
0.750 0.5010 0.03001 0.01782 -0.0832 0.5025 0.3922
1.000 0.5302 0.02994 0.01764 -0.0830 0.4969 0.4073
1.250 0.5496 0.03037 0.01822 -0.0820 0.4886 0.4215
1.500 0.5742 0.03049 0.01840 -0.0813 0.4818 0.4392
1.750 0.6028 0.03039 0.01830 -0.0810 0.4767 0.4631
2.000 0.6198 0.03096 0.01909 -0.0797 0.4686 0.4877
2.250 0.6423 0.03112 0.01943 -0.0788 0.4623 0.5218
2.500 0.6682 0.03100 0.01946 -0.0779 0.4576 0.5725
2.750 0.6819 0.03146 0.02030 -0.0757 0.4508 0.6357
3.000 0.6950 0.03163 0.02088 -0.0727 0.4446 0.7372
3.250 0.7303 0.03144 0.02081 -0.0732 0.4392 1.0000
3.500 0.7529 0.03214 0.02135 -0.0727 0.4338 1.0000
3.750 0.7670 0.03327 0.02246 -0.0715 0.4269 1.0000
4.000 0.7915 0.03380 0.02283 -0.0711 0.4217 1.0000
4.250 0.8224 0.03401 0.02281 -0.0712 0.4178 1.0000
4.500 0.8274 0.03567 0.02457 -0.0692 0.4110 1.0000
4.750 0.8427 0.03673 0.02561 -0.0680 0.4053 1.0000
5.000 0.8692 0.03715 0.02588 -0.0677 0.4011 1.0000
5.250 0.8977 0.03751 0.02608 -0.0676 0.3974 1.0000
5.500 0.8845 0.04023 0.02901 -0.0643 0.3900 1.0000
5.750 0.8976 0.04142 0.03019 -0.0630 0.3852 1.0000
6.000 0.9262 0.04173 0.03037 -0.0628 0.3816 1.0000
6.250 0.9441 0.04272 0.03130 -0.0619 0.3777 1.0000
6.500 0.8822 0.04836 0.03725 -0.0561 0.3689 1.0000
6.750 0.8970 0.04951 0.03835 -0.0552 0.3648 1.0000
7.000 0.9309 0.04939 0.03813 -0.0551 0.3623 1.0000
7.500 0.8323 0.06390 0.05292 -0.0535 0.3445 1.0000
7.750 0.8646 0.06334 0.05229 -0.0526 0.3429 1.0000
9.250 0.7526 0.09975 0.08901 -0.0612 0.3023 1.0000
9.500 0.7485 0.10403 0.09332 -0.0623 0.2971 1.0000
9.750 0.7609 0.10621 0.09549 -0.0624 0.2939 1.0000
10.000 0.7780 0.10785 0.09711 -0.0623 0.2918 1.0000
10.500 0.7592 0.11825 0.10760 -0.0657 0.2823 1.0000
10.750 0.7670 0.12108 0.11044 -0.0663 0.2787 1.0000
11.000 0.7802 0.12331 0.11269 -0.0665 0.2763 1.0000
11.250 0.7981 0.12495 0.11431 -0.0664 0.2745 1.0000
11.500 0.7846 0.13075 0.12018 -0.0688 0.2699 1.0000
11.750 0.7812 0.13503 0.12451 -0.0705 0.2656 1.0000
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Polar data table (+)
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