EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 100,000 Max Cl/Cd: 33.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1211-il-100000.txt Download as CSV file: xf-e1211-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2189 0.11711 0.11199 -0.0316 1.0000 0.1739
-10.500 -0.2137 0.11515 0.11008 -0.0315 1.0000 0.1823
-10.250 -0.2658 0.11414 0.10920 -0.0360 1.0000 0.1851
-10.000 -0.2036 0.10946 0.10449 -0.0312 1.0000 0.1917
-9.750 -0.2265 0.10847 0.10361 -0.0327 1.0000 0.1998
-9.500 -0.2433 0.10535 0.10061 -0.0335 1.0000 0.2020
-9.250 -0.2032 0.10238 0.09765 -0.0304 1.0000 0.2069
-9.000 -0.2073 0.10110 0.09650 -0.0290 1.0000 0.2130
-8.500 -0.1879 0.09485 0.09038 -0.0359 0.9814 0.2232
-8.250 -0.2082 0.09182 0.08734 -0.0506 0.9512 0.2361
-8.000 -0.1405 0.08618 0.08163 -0.0494 0.9416 0.2397
-7.750 -0.0943 0.08256 0.07792 -0.0549 0.9262 0.2503
-7.500 -0.0750 0.07760 0.07286 -0.0641 0.9069 0.2585
-7.250 -0.0203 0.07425 0.06934 -0.0687 0.8861 0.2683
-7.000 -0.0989 0.06190 0.05679 -0.0860 0.8595 0.2374
-6.750 -0.0760 0.05915 0.05390 -0.0869 0.8390 0.2387
-6.500 -0.0765 0.05383 0.04841 -0.0906 0.8198 0.2309
-6.250 -0.0980 0.04623 0.04050 -0.0966 0.8031 0.2301
-6.000 -0.1162 0.03819 0.03165 -0.1022 0.7896 0.2354
-5.750 -0.0920 0.03734 0.03078 -0.1012 0.7749 0.2393
-5.500 -0.0681 0.03741 0.03088 -0.0996 0.7590 0.2435
-5.250 -0.0500 0.03560 0.02879 -0.0998 0.7461 0.2489
-5.000 -0.0348 0.03295 0.02547 -0.1009 0.7335 0.2553
-4.750 -0.0120 0.03217 0.02478 -0.0999 0.7203 0.2591
-4.500 0.0140 0.03175 0.02427 -0.0991 0.7089 0.2636
-4.250 0.0354 0.03085 0.02320 -0.0987 0.6958 0.2689
-4.000 0.0605 0.02958 0.02138 -0.0992 0.6861 0.2750
-3.750 0.0824 0.02878 0.02062 -0.0983 0.6733 0.2792
-3.500 0.1098 0.02841 0.02014 -0.0978 0.6639 0.2840
-3.250 0.1328 0.02788 0.01952 -0.0972 0.6515 0.2893
-3.000 0.1609 0.02723 0.01842 -0.0974 0.6429 0.2954
-2.750 0.1837 0.02665 0.01788 -0.0967 0.6310 0.2999
-2.500 0.2115 0.02629 0.01740 -0.0963 0.6224 0.3051
-2.250 0.2357 0.02604 0.01709 -0.0957 0.6115 0.3108
-2.000 0.2640 0.02570 0.01640 -0.0957 0.6028 0.3171
-1.750 0.2886 0.02532 0.01607 -0.0951 0.5932 0.3219
-1.500 0.3151 0.02510 0.01579 -0.0946 0.5840 0.3280
-1.250 0.3429 0.02496 0.01547 -0.0944 0.5761 0.3350
-1.000 0.3680 0.02477 0.01522 -0.0939 0.5664 0.3409
-0.750 0.3966 0.02453 0.01490 -0.0937 0.5593 0.3475
-0.500 0.4207 0.02458 0.01496 -0.0930 0.5500 0.3551
-0.250 0.4482 0.02443 0.01468 -0.0927 0.5421 0.3628
0.000 0.4760 0.02436 0.01459 -0.0924 0.5355 0.3706
0.250 0.4998 0.02447 0.01473 -0.0917 0.5265 0.3799
0.500 0.5279 0.02431 0.01453 -0.0914 0.5197 0.3895
0.750 0.5535 0.02446 0.01468 -0.0909 0.5125 0.4007
1.000 0.5778 0.02451 0.01483 -0.0902 0.5046 0.4117
1.250 0.6068 0.02450 0.01470 -0.0901 0.4987 0.4275
1.500 0.6306 0.02469 0.01504 -0.0893 0.4919 0.4433
1.750 0.6543 0.02480 0.01529 -0.0885 0.4844 0.4625
2.000 0.6826 0.02474 0.01523 -0.0882 0.4788 0.4898
2.250 0.7058 0.02494 0.01565 -0.0873 0.4729 0.5239
2.500 0.7264 0.02511 0.01616 -0.0860 0.4659 0.5757
2.750 0.7489 0.02484 0.01628 -0.0844 0.4605 0.6766
3.000 0.7825 0.02433 0.01625 -0.0837 0.4555 1.0000
3.250 0.8015 0.02512 0.01703 -0.0828 0.4483 1.0000
3.500 0.8275 0.02558 0.01735 -0.0826 0.4426 1.0000
3.750 0.8580 0.02588 0.01740 -0.0828 0.4382 1.0000
4.000 0.8773 0.02675 0.01829 -0.0818 0.4323 1.0000
4.250 0.8977 0.02746 0.01902 -0.0808 0.4262 1.0000
4.500 0.9250 0.02784 0.01927 -0.0806 0.4214 1.0000
4.750 0.9566 0.02824 0.01944 -0.0810 0.4177 1.0000
5.000 0.9670 0.02954 0.02094 -0.0790 0.4117 1.0000
5.250 0.9868 0.03033 0.02175 -0.0780 0.4062 1.0000
5.500 1.0146 0.03068 0.02198 -0.0778 0.4019 1.0000
5.750 1.0477 0.03102 0.02212 -0.0783 0.3984 1.0000
6.000 1.0497 0.03283 0.02421 -0.0756 0.3928 1.0000
6.250 1.0640 0.03401 0.02546 -0.0741 0.3879 1.0000
6.500 1.0897 0.03451 0.02590 -0.0738 0.3839 1.0000
6.750 1.1238 0.03467 0.02589 -0.0743 0.3805 1.0000
7.000 1.1247 0.03670 0.02812 -0.0716 0.3757 1.0000
7.250 1.1189 0.03902 0.03065 -0.0684 0.3705 1.0000
7.500 1.1369 0.04001 0.03164 -0.0675 0.3667 1.0000
7.750 1.1675 0.04030 0.03186 -0.0676 0.3637 1.0000
8.000 1.2099 0.04028 0.03164 -0.0689 0.3609 1.0000
8.250 0.8507 0.07446 0.06689 -0.0580 0.3430 1.0000
8.500 0.9099 0.06987 0.06222 -0.0556 0.3428 1.0000
8.750 0.9747 0.06486 0.05712 -0.0533 0.3427 1.0000
9.000 1.0655 0.05822 0.05033 -0.0522 0.3429 1.0000
9.500 0.6062 0.12825 0.12124 -0.0782 0.3688 1.0000
9.750 0.6253 0.13057 0.12353 -0.0783 0.3650 1.0000
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Polar data table (+)
Polar graphs
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