EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 50,000 Max Cl/Cd: 19.4 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea81006-il-50000-n5.txt Download as CSV file: xf-ea81006-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 8(-1)-006 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6658 0.09119 0.08422 -0.0025 1.0000 0.0499
-8.750 -0.6730 0.08545 0.07855 -0.0069 1.0000 0.0487
-8.250 -0.7049 0.07247 0.06533 -0.0149 1.0000 0.0449
-8.000 -0.7061 0.06775 0.06041 -0.0155 1.0000 0.0449
-7.750 -0.6945 0.06479 0.05748 -0.0147 1.0000 0.0475
-7.500 -0.6905 0.06093 0.05343 -0.0149 1.0000 0.0502
-7.250 -0.6873 0.05637 0.04850 -0.0150 1.0000 0.0525
-7.000 -0.6820 0.05167 0.04323 -0.0146 1.0000 0.0543
-6.750 -0.6735 0.04722 0.03801 -0.0136 1.0000 0.0554
-6.500 -0.6578 0.04362 0.03423 -0.0128 1.0000 0.0575
-6.250 -0.6420 0.04008 0.03012 -0.0116 1.0000 0.0607
-6.000 -0.6253 0.03729 0.02673 -0.0105 1.0000 0.0687
-5.750 -0.6050 0.03447 0.02355 -0.0096 1.0000 0.0739
-5.500 -0.5823 0.03181 0.02043 -0.0085 1.0000 0.0775
-5.250 -0.5599 0.02984 0.01822 -0.0078 1.0000 0.0855
-5.000 -0.5351 0.02807 0.01617 -0.0070 1.0000 0.0902
-4.750 -0.5097 0.02637 0.01419 -0.0062 1.0000 0.0939
-4.500 -0.4846 0.02499 0.01274 -0.0055 1.0000 0.0987
-4.250 -0.4588 0.02385 0.01143 -0.0047 1.0000 0.1013
-4.000 -0.4335 0.02293 0.01030 -0.0039 1.0000 0.1053
-3.750 -0.4094 0.02196 0.00932 -0.0031 1.0000 0.1094
-3.500 -0.3855 0.02119 0.00844 -0.0022 1.0000 0.1129
-3.250 -0.3619 0.02048 0.00761 -0.0014 1.0000 0.1184
-3.000 -0.3393 0.01982 0.00694 -0.0004 1.0000 0.1260
-2.750 -0.3170 0.01917 0.00637 0.0006 1.0000 0.1364
-2.500 -0.2951 0.01847 0.00587 0.0016 1.0000 0.1633
-2.250 -0.2751 0.01750 0.00536 0.0027 1.0000 0.2620
-2.000 -0.2649 0.01562 0.00520 0.0063 1.0000 0.5729
-1.750 -0.2166 0.01522 0.00554 0.0053 1.0000 0.8726
-1.500 -0.1128 0.01530 0.00525 -0.0085 1.0000 0.9917
-1.250 -0.0840 0.01517 0.00498 -0.0091 1.0000 1.0000
-1.000 -0.0668 0.01507 0.00480 -0.0074 1.0000 1.0000
-0.750 -0.0498 0.01499 0.00466 -0.0056 1.0000 1.0000
-0.500 -0.0331 0.01494 0.00455 -0.0038 1.0000 1.0000
-0.250 -0.0166 0.01490 0.00449 -0.0019 1.0000 1.0000
0.000 0.0000 0.01489 0.00447 0.0000 1.0000 1.0000
0.250 0.0166 0.01490 0.00449 0.0019 1.0000 1.0000
0.500 0.0332 0.01493 0.00455 0.0038 1.0000 1.0000
0.750 0.0498 0.01499 0.00466 0.0056 1.0000 1.0000
1.000 0.0668 0.01507 0.00480 0.0074 1.0000 1.0000
1.250 0.0840 0.01517 0.00498 0.0091 1.0000 1.0000
1.500 0.1126 0.01530 0.00525 0.0085 0.9919 1.0000
1.750 0.2166 0.01522 0.00554 -0.0053 0.8726 1.0000
2.000 0.2649 0.01562 0.00520 -0.0063 0.5729 1.0000
2.250 0.2751 0.01749 0.00536 -0.0027 0.2628 1.0000
2.500 0.2951 0.01847 0.00587 -0.0016 0.1633 1.0000
2.750 0.3170 0.01917 0.00637 -0.0006 0.1363 1.0000
3.000 0.3393 0.01982 0.00694 0.0004 0.1261 1.0000
3.250 0.3619 0.02048 0.00761 0.0014 0.1184 1.0000
3.500 0.3855 0.02119 0.00844 0.0022 0.1129 1.0000
3.750 0.4094 0.02196 0.00932 0.0031 0.1095 1.0000
4.000 0.4335 0.02292 0.01030 0.0039 0.1054 1.0000
4.250 0.4588 0.02385 0.01143 0.0047 0.1014 1.0000
4.500 0.4846 0.02498 0.01274 0.0055 0.0987 1.0000
4.750 0.5096 0.02637 0.01419 0.0063 0.0939 1.0000
5.000 0.5350 0.02806 0.01617 0.0070 0.0902 1.0000
5.250 0.5598 0.02984 0.01822 0.0078 0.0856 1.0000
5.500 0.5823 0.03181 0.02042 0.0085 0.0775 1.0000
5.750 0.6049 0.03447 0.02356 0.0096 0.0739 1.0000
6.000 0.6252 0.03729 0.02674 0.0105 0.0687 1.0000
6.250 0.6419 0.04009 0.03013 0.0116 0.0606 1.0000
6.500 0.6578 0.04360 0.03422 0.0128 0.0575 1.0000
6.750 0.6733 0.04723 0.03803 0.0136 0.0553 1.0000
7.000 0.6820 0.05166 0.04322 0.0146 0.0543 1.0000
7.250 0.6872 0.05637 0.04850 0.0150 0.0524 1.0000
7.500 0.6905 0.06093 0.05344 0.0149 0.0503 1.0000
7.750 0.6940 0.06492 0.05763 0.0147 0.0477 1.0000
8.000 0.7062 0.06773 0.06026 0.0155 0.0449 1.0000
8.250 0.7047 0.07249 0.06535 0.0149 0.0449 1.0000
8.750 0.6732 0.08546 0.07855 0.0069 0.0487 1.0000
9.000 0.6660 0.09119 0.08422 0.0024 0.0499 1.0000
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Polar data table (+)
Polar graphs
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