EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 100,000 Max Cl/Cd: 29.66 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e904-il-100000.txt Download as CSV file: xf-e904-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 904 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4771 0.10745 0.10252 -0.0365 1.0000 0.0753
-9.500 -0.4913 0.10461 0.09980 -0.0405 1.0000 0.0763
-9.250 -0.5070 0.10146 0.09675 -0.0443 1.0000 0.0767
-9.000 -0.4884 0.09639 0.09167 -0.0393 1.0000 0.0791
-8.750 -0.4847 0.09317 0.08849 -0.0379 1.0000 0.0823
-8.500 -0.4914 0.08999 0.08538 -0.0384 1.0000 0.0847
-8.250 -0.5056 0.08689 0.08239 -0.0394 1.0000 0.0865
-8.000 -0.5256 0.08445 0.08003 -0.0386 1.0000 0.0871
-7.750 -0.5530 0.08258 0.07823 -0.0363 1.0000 0.0883
-7.500 -0.5763 0.08094 0.07657 -0.0339 1.0000 0.0891
-7.250 -0.6051 0.07999 0.07546 -0.0311 1.0000 0.0898
-7.000 -0.6000 0.07465 0.07027 -0.0289 1.0000 0.0917
-6.750 -0.5977 0.07175 0.06742 -0.0259 1.0000 0.0946
-6.500 -0.6039 0.06906 0.06467 -0.0237 1.0000 0.0990
-6.250 -0.6203 0.06674 0.06199 -0.0221 1.0000 0.1040
-6.000 -0.6119 0.06274 0.05815 -0.0197 1.0000 0.1075
-5.500 -0.6080 0.05667 0.05184 -0.0157 1.0000 0.1215
-5.250 -0.6040 0.05382 0.04886 -0.0138 1.0000 0.1341
-5.000 -0.6011 0.05150 0.04633 -0.0116 1.0000 0.1579
-4.750 -0.5917 0.04858 0.04347 -0.0094 1.0000 0.1743
-4.500 -0.5558 0.03950 0.03231 -0.0073 1.0000 0.0647
-4.250 -0.5371 0.03559 0.02832 -0.0059 1.0000 0.0599
-4.000 -0.5136 0.03212 0.02406 -0.0034 1.0000 0.0495
-3.750 -0.4910 0.02881 0.02031 -0.0017 1.0000 0.0454
-3.500 -0.4657 0.02613 0.01704 0.0001 1.0000 0.0422
-3.250 -0.4406 0.02408 0.01469 0.0016 1.0000 0.0418
-3.000 -0.4171 0.02251 0.01287 0.0030 1.0000 0.0425
-2.750 -0.3951 0.02114 0.01144 0.0046 1.0000 0.0460
-2.500 -0.1795 0.01804 0.01155 -0.0248 1.0000 1.0000
-2.250 -0.1708 0.01793 0.01122 -0.0221 1.0000 1.0000
-2.000 -0.1616 0.01784 0.01093 -0.0194 1.0000 1.0000
-1.750 -0.1518 0.01778 0.01059 -0.0167 1.0000 1.0000
-1.500 -0.1417 0.01772 0.01037 -0.0141 1.0000 1.0000
-1.250 -0.1314 0.01769 0.01018 -0.0115 1.0000 1.0000
-1.000 -0.1207 0.01766 0.01002 -0.0090 1.0000 1.0000
-0.750 -0.1099 0.01765 0.00990 -0.0065 1.0000 1.0000
-0.500 -0.0989 0.01765 0.00979 -0.0040 1.0000 1.0000
-0.250 -0.0875 0.01768 0.00971 -0.0017 1.0000 1.0000
0.000 -0.0756 0.01772 0.00966 0.0006 1.0000 1.0000
0.250 -0.0632 0.01779 0.00960 0.0028 1.0000 1.0000
0.500 -0.0501 0.01788 0.00962 0.0048 1.0000 1.0000
0.750 -0.0365 0.01801 0.00969 0.0066 1.0000 1.0000
1.000 -0.0224 0.01818 0.00980 0.0084 1.0000 1.0000
1.250 -0.0075 0.01839 0.00997 0.0100 1.0000 1.0000
1.500 0.0078 0.01864 0.01019 0.0114 1.0000 1.0000
1.750 0.0358 0.01915 0.01071 0.0101 0.9965 1.0000
2.000 0.0806 0.01995 0.01153 0.0056 0.9869 1.0000
2.250 0.1235 0.02068 0.01231 0.0015 0.9767 1.0000
2.500 0.1666 0.02135 0.01306 -0.0025 0.9660 1.0000
2.750 0.2103 0.02192 0.01375 -0.0064 0.9544 1.0000
3.000 0.2546 0.02238 0.01445 -0.0103 0.9413 1.0000
3.250 0.2987 0.02273 0.01499 -0.0139 0.9277 1.0000
3.500 0.3427 0.02298 0.01546 -0.0173 0.9134 1.0000
3.750 0.3863 0.02315 0.01590 -0.0204 0.8993 1.0000
4.000 0.4317 0.02318 0.01637 -0.0236 0.8846 1.0000
4.250 0.4824 0.02300 0.01665 -0.0273 0.8693 1.0000
4.500 0.6270 0.02114 0.01109 -0.0325 0.0393 1.0000
4.750 0.6391 0.02234 0.01234 -0.0293 0.0379 1.0000
5.000 0.6594 0.02402 0.01402 -0.0274 0.0369 1.0000
5.250 0.6898 0.02614 0.01625 -0.0271 0.0370 1.0000
5.500 0.7225 0.02866 0.01908 -0.0267 0.0394 1.0000
5.750 0.7497 0.03170 0.02260 -0.0254 0.0428 1.0000
6.000 0.7749 0.03566 0.02673 -0.0244 0.0467 1.0000
6.250 0.7916 0.03834 0.03012 -0.0202 0.0569 1.0000
10.250 0.6854 0.10285 0.09819 0.0065 0.1173 1.0000
10.500 0.7055 0.10599 0.10135 0.0112 0.1091 1.0000
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Polar data table (+)
Polar graphs
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