EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 200,000 Max Cl/Cd: 34.96 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea81006-il-200000.txt Download as CSV file: xf-ea81006-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6659 0.08766 0.08415 -0.0020 1.0000 0.0420
-8.750 -0.6691 0.08319 0.07971 -0.0047 1.0000 0.0426
-8.500 -0.6788 0.07809 0.07462 -0.0087 1.0000 0.0428
-8.250 -0.6842 0.07329 0.06978 -0.0112 1.0000 0.0431
-8.000 -0.6858 0.06867 0.06510 -0.0129 1.0000 0.0439
-7.750 -0.6854 0.06398 0.06031 -0.0143 1.0000 0.0447
-7.500 -0.6827 0.05931 0.05548 -0.0152 1.0000 0.0459
-7.250 -0.6776 0.05461 0.05053 -0.0157 1.0000 0.0480
-7.000 -0.6720 0.05268 0.04775 -0.0145 1.0000 0.0512
-6.750 -0.6651 0.04803 0.04267 -0.0134 1.0000 0.0517
-6.500 -0.6524 0.04139 0.03632 -0.0138 1.0000 0.0545
-6.250 -0.6369 0.03841 0.03318 -0.0129 1.0000 0.0570
-5.750 -0.6036 0.03001 0.02355 -0.0086 1.0000 0.0485
-5.250 -0.5653 0.02568 0.01866 -0.0062 1.0000 0.0598
-5.000 -0.5434 0.02339 0.01593 -0.0045 1.0000 0.0608
-4.750 -0.5225 0.02130 0.01354 -0.0033 1.0000 0.0673
-4.500 -0.4992 0.01968 0.01176 -0.0023 1.0000 0.0700
-4.250 -0.4757 0.01877 0.01066 -0.0012 1.0000 0.0746
-4.000 -0.4516 0.01780 0.00951 -0.0001 1.0000 0.0757
-3.750 -0.4277 0.01697 0.00853 0.0009 1.0000 0.0773
-3.500 -0.4043 0.01542 0.00700 0.0018 1.0000 0.0794
-3.250 -0.3811 0.01457 0.00614 0.0028 1.0000 0.0802
-3.000 -0.3585 0.01386 0.00545 0.0040 1.0000 0.0812
-2.750 -0.3364 0.01326 0.00488 0.0052 1.0000 0.0823
-2.500 -0.3146 0.01274 0.00439 0.0064 1.0000 0.0839
-2.250 -0.2929 0.01229 0.00396 0.0076 1.0000 0.0868
-2.000 -0.2711 0.01192 0.00359 0.0088 1.0000 0.0884
-1.750 -0.2491 0.01161 0.00327 0.0099 1.0000 0.0898
-1.500 -0.2271 0.01132 0.00299 0.0111 1.0000 0.0921
-1.250 -0.2050 0.01107 0.00276 0.0122 1.0000 0.0958
-1.000 -0.1828 0.01088 0.00259 0.0132 1.0000 0.1016
-0.750 -0.1616 0.01044 0.00252 0.0143 1.0000 0.1661
-0.500 -0.1418 0.00976 0.00249 0.0154 1.0000 0.3252
-0.250 -0.1146 0.00805 0.00279 0.0158 0.9911 0.8118
0.000 -0.0001 0.00801 0.00309 0.0000 0.9692 0.9692
0.250 0.1150 0.00804 0.00281 -0.0159 0.8176 0.9913
0.500 0.1416 0.00977 0.00249 -0.0154 0.3224 1.0000
0.750 0.1615 0.01044 0.00252 -0.0142 0.1656 1.0000
1.000 0.1827 0.01088 0.00259 -0.0132 0.1015 1.0000
1.250 0.2049 0.01107 0.00276 -0.0121 0.0961 1.0000
1.500 0.2270 0.01132 0.00299 -0.0110 0.0921 1.0000
1.750 0.2490 0.01161 0.00328 -0.0099 0.0898 1.0000
2.000 0.2709 0.01192 0.00359 -0.0087 0.0884 1.0000
2.250 0.2927 0.01229 0.00396 -0.0075 0.0867 1.0000
2.500 0.3144 0.01274 0.00439 -0.0063 0.0839 1.0000
2.750 0.3362 0.01326 0.00488 -0.0051 0.0823 1.0000
3.000 0.3584 0.01386 0.00545 -0.0039 0.0813 1.0000
3.250 0.3809 0.01457 0.00614 -0.0028 0.0802 1.0000
3.500 0.4041 0.01543 0.00700 -0.0018 0.0794 1.0000
3.750 0.4276 0.01698 0.00854 -0.0009 0.0773 1.0000
4.000 0.4514 0.01780 0.00951 0.0002 0.0757 1.0000
4.250 0.4756 0.01877 0.01066 0.0012 0.0746 1.0000
4.500 0.4990 0.01968 0.01176 0.0023 0.0701 1.0000
4.750 0.5224 0.02130 0.01353 0.0033 0.0673 1.0000
5.000 0.5432 0.02344 0.01598 0.0045 0.0610 1.0000
5.250 0.5652 0.02569 0.01867 0.0062 0.0598 1.0000
5.500 0.5653 0.01617 0.01042 0.0109 0.0809 1.0000
5.750 0.5807 0.01853 0.01303 0.0119 0.0687 1.0000
6.000 0.5969 0.02175 0.01612 0.0122 0.0650 1.0000
6.250 0.6076 0.02526 0.02045 0.0142 0.0581 1.0000
6.500 0.6206 0.02872 0.02415 0.0151 0.0554 1.0000
7.000 0.6723 0.05277 0.04782 0.0144 0.0513 1.0000
7.250 0.6779 0.05459 0.05052 0.0157 0.0481 1.0000
7.500 0.6829 0.05934 0.05551 0.0152 0.0460 1.0000
7.750 0.6858 0.06402 0.06035 0.0142 0.0448 1.0000
8.000 0.6861 0.06873 0.06517 0.0128 0.0440 1.0000
8.250 0.6846 0.07335 0.06984 0.0111 0.0431 1.0000
8.500 0.6796 0.07808 0.07462 0.0087 0.0427 1.0000
8.750 0.6696 0.08327 0.07979 0.0045 0.0427 1.0000
9.000 0.6664 0.08776 0.08424 0.0018 0.0421 1.0000
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Polar data table (+)
Polar graphs
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