EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 8(-1)-006 AIRFOIL (ea81006-il) Reynolds number: 200,000 Max Cl/Cd: 35.75 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea81006-il-200000-n5.txt Download as CSV file: xf-ea81006-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6915 0.08963 0.08614 0.0026 1.0000 0.0115
-9.500 -0.6986 0.08392 0.08049 -0.0009 1.0000 0.0116
-9.250 -0.7155 0.07603 0.07267 -0.0070 1.0000 0.0112
-9.000 -0.7421 0.06733 0.06395 -0.0130 1.0000 0.0109
-8.750 -0.7640 0.05799 0.05443 -0.0161 1.0000 0.0105
-8.500 -0.7780 0.04982 0.04593 -0.0168 1.0000 0.0105
-8.250 -0.7828 0.04337 0.03908 -0.0162 1.0000 0.0107
-8.000 -0.7745 0.03988 0.03528 -0.0153 1.0000 0.0113
-7.750 -0.7601 0.03773 0.03289 -0.0145 1.0000 0.0124
-7.500 -0.7514 0.03303 0.02767 -0.0129 1.0000 0.0135
-7.250 -0.7457 0.02572 0.01941 -0.0101 1.0000 0.0146
-7.000 -0.7291 0.02183 0.01487 -0.0083 1.0000 0.0161
-6.750 -0.7082 0.01982 0.01252 -0.0071 1.0000 0.0177
-6.500 -0.6837 0.01988 0.01259 -0.0067 1.0000 0.0203
-6.250 -0.6590 0.01991 0.01248 -0.0061 1.0000 0.0242
-5.750 -0.6108 0.01921 0.01134 -0.0046 1.0000 0.0341
-5.500 -0.5870 0.01935 0.01129 -0.0039 1.0000 0.0388
-5.250 -0.5636 0.01914 0.01103 -0.0032 1.0000 0.0421
-5.000 -0.5406 0.01864 0.01035 -0.0024 1.0000 0.0465
-4.750 -0.5175 0.01794 0.00960 -0.0017 1.0000 0.0494
-4.500 -0.4941 0.01734 0.00883 -0.0008 1.0000 0.0525
-4.250 -0.4705 0.01668 0.00804 0.0001 1.0000 0.0538
-4.000 -0.4469 0.01610 0.00735 0.0010 1.0000 0.0548
-3.750 -0.4236 0.01554 0.00674 0.0020 1.0000 0.0556
-3.500 -0.4013 0.01474 0.00603 0.0029 1.0000 0.0571
-3.250 -0.3789 0.01420 0.00549 0.0039 1.0000 0.0585
-3.000 -0.3567 0.01372 0.00503 0.0050 1.0000 0.0594
-2.750 -0.3348 0.01329 0.00461 0.0061 1.0000 0.0603
-2.500 -0.3129 0.01291 0.00425 0.0072 1.0000 0.0613
-2.250 -0.2909 0.01262 0.00396 0.0083 1.0000 0.0627
-2.000 -0.2697 0.01222 0.00360 0.0094 1.0000 0.0641
-1.750 -0.2480 0.01193 0.00334 0.0105 1.0000 0.0654
-1.500 -0.2045 0.01164 0.00307 0.0070 0.9905 0.0672
-1.250 -0.1592 0.01136 0.00280 0.0032 0.9777 0.0698
-1.000 -0.1168 0.01106 0.00253 0.0002 0.9618 0.0734
-0.750 -0.0726 0.01079 0.00228 -0.0030 0.9310 0.0775
-0.500 -0.0333 0.01052 0.00202 -0.0050 0.8778 0.0884
-0.250 -0.0075 0.00991 0.00181 -0.0043 0.7928 0.2521
0.000 0.0000 0.00902 0.00157 0.0000 0.5977 0.5973
0.250 0.0075 0.00990 0.00181 0.0043 0.2529 0.7936
0.500 0.0333 0.01052 0.00202 0.0050 0.0884 0.8776
0.750 0.0724 0.01078 0.00228 0.0031 0.0775 0.9307
1.000 0.1167 0.01106 0.00253 -0.0001 0.0734 0.9617
1.250 0.1590 0.01136 0.00280 -0.0032 0.0698 0.9776
1.500 0.2039 0.01164 0.00307 -0.0069 0.0672 0.9902
1.750 0.2480 0.01193 0.00334 -0.0105 0.0654 1.0000
2.000 0.2697 0.01222 0.00360 -0.0094 0.0640 1.0000
2.250 0.2909 0.01262 0.00396 -0.0083 0.0627 1.0000
2.500 0.3129 0.01292 0.00425 -0.0072 0.0614 1.0000
2.750 0.3347 0.01329 0.00461 -0.0061 0.0603 1.0000
3.000 0.3567 0.01372 0.00503 -0.0050 0.0594 1.0000
3.250 0.3789 0.01420 0.00549 -0.0039 0.0585 1.0000
3.500 0.4012 0.01474 0.00603 -0.0029 0.0571 1.0000
3.750 0.4235 0.01553 0.00673 -0.0020 0.0556 1.0000
4.000 0.4468 0.01610 0.00735 -0.0010 0.0548 1.0000
4.250 0.4704 0.01668 0.00804 -0.0001 0.0539 1.0000
4.500 0.4940 0.01733 0.00883 0.0008 0.0525 1.0000
4.750 0.5174 0.01794 0.00960 0.0017 0.0494 1.0000
5.000 0.5405 0.01864 0.01035 0.0024 0.0465 1.0000
5.250 0.5635 0.01913 0.01102 0.0032 0.0421 1.0000
5.500 0.5869 0.01937 0.01132 0.0039 0.0389 1.0000
5.750 0.6108 0.01919 0.01132 0.0046 0.0341 1.0000
6.250 0.6590 0.01988 0.01244 0.0061 0.0241 1.0000
6.500 0.6836 0.01989 0.01260 0.0067 0.0203 1.0000
6.750 0.7082 0.01981 0.01250 0.0071 0.0177 1.0000
7.000 0.7290 0.02182 0.01486 0.0083 0.0161 1.0000
7.250 0.7457 0.02569 0.01938 0.0101 0.0146 1.0000
7.500 0.7515 0.03296 0.02759 0.0129 0.0135 1.0000
7.750 0.7592 0.03797 0.03314 0.0146 0.0124 1.0000
8.000 0.7697 0.04129 0.03680 0.0156 0.0115 1.0000
8.250 0.7817 0.04364 0.03937 0.0162 0.0107 1.0000
8.500 0.7766 0.05018 0.04631 0.0168 0.0105 1.0000
8.750 0.7652 0.05762 0.05405 0.0162 0.0105 1.0000
9.000 0.7434 0.06700 0.06362 0.0131 0.0108 1.0000
9.250 0.7146 0.07630 0.07293 0.0068 0.0113 1.0000
9.500 0.6922 0.08571 0.08225 -0.0002 0.0124 1.0000
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Polar data table (+)
Polar graphs
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