EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 50,000 Max Cl/Cd: 21.59 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e904-il-50000.txt Download as CSV file: xf-e904-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4783 0.09933 0.09282 -0.0234 1.0000 0.2571
-8.250 -0.4804 0.09636 0.08994 -0.0222 1.0000 0.2701
-8.000 -0.4834 0.09349 0.08716 -0.0207 1.0000 0.2836
-7.750 -0.4939 0.09108 0.08488 -0.0188 1.0000 0.3005
-7.500 -0.5051 0.08898 0.08290 -0.0165 1.0000 0.3150
-7.250 -0.4968 0.08532 0.07930 -0.0137 1.0000 0.3347
-5.250 -0.5845 0.05332 0.04611 -0.0173 1.0000 0.1252
-5.000 -0.5709 0.04854 0.04055 -0.0155 1.0000 0.1011
-4.750 -0.5360 0.03242 0.02482 -0.0139 1.0000 0.0951
-4.500 -0.5208 0.02866 0.02038 -0.0119 1.0000 0.0873
-4.250 -0.5038 0.02496 0.01623 -0.0101 1.0000 0.0836
-4.000 -0.4838 0.02161 0.01231 -0.0083 1.0000 0.0811
-3.750 -0.4628 0.01902 0.00929 -0.0068 1.0000 0.0857
-3.500 -0.2008 0.02239 0.01434 -0.0376 1.0000 1.0000
-3.250 -0.1951 0.02214 0.01369 -0.0345 1.0000 1.0000
-3.000 -0.1883 0.02195 0.01313 -0.0316 1.0000 1.0000
-2.750 -0.1805 0.02178 0.01261 -0.0287 1.0000 1.0000
-2.500 -0.1720 0.02165 0.01218 -0.0259 1.0000 1.0000
-2.250 -0.1629 0.02154 0.01178 -0.0232 1.0000 1.0000
-2.000 -0.1533 0.02146 0.01129 -0.0205 1.0000 1.0000
-1.750 -0.1432 0.02139 0.01100 -0.0179 1.0000 1.0000
-1.500 -0.1326 0.02134 0.01073 -0.0154 1.0000 1.0000
-1.250 -0.1218 0.02131 0.01049 -0.0129 1.0000 1.0000
-1.000 -0.1105 0.02130 0.01030 -0.0104 1.0000 1.0000
-0.750 -0.0988 0.02130 0.01014 -0.0081 1.0000 1.0000
-0.500 -0.0867 0.02132 0.01000 -0.0058 1.0000 1.0000
-0.250 -0.0742 0.02136 0.00991 -0.0036 1.0000 1.0000
0.000 -0.0612 0.02143 0.00978 -0.0015 1.0000 1.0000
0.250 -0.0479 0.02151 0.00976 0.0004 1.0000 1.0000
0.500 -0.0341 0.02163 0.00978 0.0024 1.0000 1.0000
0.750 -0.0200 0.02177 0.00983 0.0042 1.0000 1.0000
1.000 -0.0054 0.02194 0.00993 0.0058 1.0000 1.0000
1.250 0.0097 0.02214 0.01009 0.0074 1.0000 1.0000
1.500 0.0251 0.02237 0.01030 0.0089 1.0000 1.0000
1.750 0.0409 0.02264 0.01056 0.0102 1.0000 1.0000
2.000 0.0570 0.02295 0.01087 0.0114 1.0000 1.0000
2.250 0.0732 0.02329 0.01122 0.0126 1.0000 1.0000
2.500 0.0895 0.02368 0.01164 0.0136 1.0000 1.0000
2.750 0.1058 0.02410 0.01212 0.0146 1.0000 1.0000
3.000 0.1221 0.02458 0.01267 0.0155 1.0000 1.0000
3.250 0.1383 0.02510 0.01328 0.0163 1.0000 1.0000
3.500 0.1543 0.02568 0.01397 0.0171 1.0000 1.0000
3.750 0.1700 0.02633 0.01486 0.0177 1.0000 1.0000
4.000 0.1853 0.02704 0.01571 0.0183 1.0000 1.0000
4.250 0.2001 0.02783 0.01667 0.0188 1.0000 1.0000
4.500 0.2144 0.02871 0.01773 0.0193 1.0000 1.0000
4.750 0.2614 0.03070 0.02009 0.0130 0.9842 1.0000
5.000 0.3336 0.03287 0.02289 0.0025 0.9478 1.0000
5.250 0.4002 0.03434 0.02525 -0.0056 0.9099 1.0000
5.500 0.6764 0.03133 0.01961 -0.0169 0.0810 1.0000
5.750 0.7198 0.03421 0.02278 -0.0181 0.0758 1.0000
6.000 0.7518 0.03798 0.02676 -0.0185 0.0710 1.0000
6.250 0.7739 0.04088 0.03009 -0.0166 0.0708 1.0000
6.500 0.7906 0.04307 0.03304 -0.0131 0.0743 1.0000
6.750 0.8040 0.04637 0.03692 -0.0099 0.0792 1.0000
7.000 0.8209 0.05091 0.04159 -0.0081 0.0835 1.0000
7.250 0.8214 0.05334 0.04493 -0.0029 0.0918 1.0000
7.500 0.8265 0.05715 0.04924 0.0005 0.1015 1.0000
7.750 0.8274 0.06139 0.05396 0.0038 0.1142 1.0000
8.000 0.8352 0.06720 0.06011 0.0055 0.1368 1.0000
8.250 0.8115 0.07107 0.06449 0.0087 0.1529 1.0000
8.500 0.7935 0.07768 0.07142 0.0085 0.1902 1.0000
8.750 0.7609 0.08113 0.07492 0.0100 0.1925 1.0000
9.000 0.7293 0.08636 0.08014 0.0084 0.2061 1.0000
9.250 0.6512 0.07828 0.07232 0.0190 0.1522 1.0000
9.500 0.6217 0.08434 0.07834 0.0162 0.1535 1.0000
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Polar data table (+)
Polar graphs
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