EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 50,000 Max Cl/Cd: 23.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e904-il-50000-n5.txt Download as CSV file: xf-e904-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4765 0.09849 0.09155 -0.0403 1.0000 0.0309
-9.000 -0.4784 0.09497 0.08810 -0.0408 1.0000 0.0300
-8.750 -0.4846 0.09099 0.08421 -0.0423 1.0000 0.0302
-8.500 -0.4928 0.08710 0.08041 -0.0438 1.0000 0.0303
-8.250 -0.5000 0.08391 0.07730 -0.0435 1.0000 0.0281
-8.000 -0.5144 0.08083 0.07431 -0.0425 1.0000 0.0277
-7.750 -0.5281 0.07788 0.07142 -0.0408 1.0000 0.0268
-7.500 -0.5403 0.07489 0.06845 -0.0390 1.0000 0.0265
-7.250 -0.5520 0.07179 0.06533 -0.0368 1.0000 0.0256
-7.000 -0.5619 0.06881 0.06230 -0.0344 1.0000 0.0254
-6.750 -0.5703 0.06559 0.05897 -0.0319 1.0000 0.0247
-6.500 -0.5763 0.06214 0.05535 -0.0293 1.0000 0.0236
-6.250 -0.5791 0.05908 0.05210 -0.0267 1.0000 0.0238
-6.000 -0.5792 0.05625 0.04908 -0.0242 1.0000 0.0251
-5.750 -0.5768 0.05312 0.04567 -0.0217 1.0000 0.0257
-5.500 -0.5716 0.04999 0.04222 -0.0193 1.0000 0.0260
-5.250 -0.5638 0.04682 0.03867 -0.0170 1.0000 0.0262
-5.000 -0.5533 0.04381 0.03523 -0.0147 1.0000 0.0269
-4.750 -0.5400 0.04078 0.03173 -0.0125 1.0000 0.0275
-4.500 -0.5238 0.03791 0.02835 -0.0104 1.0000 0.0276
-4.250 -0.5047 0.03515 0.02488 -0.0085 1.0000 0.0276
-4.000 -0.4833 0.03280 0.02205 -0.0068 1.0000 0.0278
-3.750 -0.4597 0.03062 0.01942 -0.0053 1.0000 0.0287
-3.500 -0.4349 0.02872 0.01712 -0.0037 1.0000 0.0304
-3.250 -0.4109 0.02731 0.01535 -0.0022 1.0000 0.0325
-3.000 -0.3875 0.02582 0.01371 -0.0011 1.0000 0.0391
-2.750 -0.3647 0.02464 0.01251 -0.0001 1.0000 0.0638
-2.500 -0.1722 0.02173 0.01234 -0.0259 1.0000 1.0000
-2.250 -0.1630 0.02161 0.01174 -0.0232 1.0000 1.0000
-2.000 -0.1533 0.02152 0.01138 -0.0205 1.0000 1.0000
-1.750 -0.1431 0.02146 0.01108 -0.0179 1.0000 1.0000
-1.500 -0.1326 0.02141 0.01081 -0.0154 1.0000 1.0000
-1.250 -0.1217 0.02137 0.01057 -0.0129 1.0000 1.0000
-1.000 -0.1104 0.02136 0.01039 -0.0105 1.0000 1.0000
-0.750 -0.0987 0.02136 0.01022 -0.0081 1.0000 1.0000
-0.500 -0.0867 0.02139 0.01009 -0.0058 1.0000 1.0000
-0.250 -0.0742 0.02143 0.00999 -0.0036 1.0000 1.0000
0.000 -0.0612 0.02149 0.00983 -0.0015 1.0000 1.0000
0.250 -0.0479 0.02158 0.00981 0.0005 1.0000 1.0000
0.500 -0.0178 0.02191 0.01003 -0.0009 0.9950 1.0000
0.750 0.0121 0.02223 0.01028 -0.0023 0.9893 1.0000
1.000 0.0431 0.02264 0.01063 -0.0039 0.9835 1.0000
1.250 0.0725 0.02298 0.01095 -0.0051 0.9772 1.0000
1.500 0.1040 0.02339 0.01136 -0.0067 0.9707 1.0000
1.750 0.1329 0.02372 0.01172 -0.0079 0.9633 1.0000
2.000 0.1670 0.02418 0.01224 -0.0100 0.9565 1.0000
2.250 0.1951 0.02448 0.01262 -0.0108 0.9475 1.0000
2.500 0.2269 0.02486 0.01312 -0.0123 0.9390 1.0000
2.750 0.2637 0.02529 0.01372 -0.0147 0.9305 1.0000
3.000 0.2939 0.02559 0.01441 -0.0157 0.9195 1.0000
3.250 0.3267 0.02589 0.01494 -0.0171 0.9079 1.0000
3.500 0.3616 0.02614 0.01550 -0.0188 0.8952 1.0000
3.750 0.3986 0.02632 0.01601 -0.0206 0.8813 1.0000
4.000 0.4387 0.02639 0.01650 -0.0228 0.8664 1.0000
4.250 0.4737 0.02637 0.01697 -0.0237 0.8492 1.0000
4.500 0.5074 0.02626 0.01763 -0.0241 0.8301 1.0000
4.750 0.5449 0.02275 0.01475 -0.0185 0.7144 1.0000
5.000 0.5830 0.02643 0.01395 -0.0156 0.0512 1.0000
5.250 0.5986 0.02781 0.01557 -0.0130 0.0433 1.0000
5.500 0.6184 0.02948 0.01740 -0.0113 0.0368 1.0000
5.750 0.6447 0.03116 0.01927 -0.0108 0.0286 1.0000
6.000 0.6843 0.03401 0.02236 -0.0119 0.0260 1.0000
6.250 0.7172 0.03668 0.02544 -0.0118 0.0250 1.0000
6.500 0.7427 0.03964 0.02885 -0.0105 0.0243 1.0000
6.750 0.7610 0.04252 0.03217 -0.0084 0.0240 1.0000
7.000 0.7743 0.04553 0.03562 -0.0057 0.0239 1.0000
7.250 0.7834 0.04865 0.03917 -0.0026 0.0240 1.0000
7.500 0.7893 0.05173 0.04262 0.0005 0.0242 1.0000
7.750 0.7923 0.05488 0.04612 0.0037 0.0244 1.0000
8.000 0.7924 0.05812 0.04988 0.0069 0.0247 1.0000
8.250 0.7903 0.06135 0.05338 0.0099 0.0250 1.0000
8.500 0.7846 0.06478 0.05705 0.0130 0.0253 1.0000
8.750 0.7774 0.06808 0.06055 0.0158 0.0256 1.0000
9.000 0.7672 0.07132 0.06394 0.0185 0.0259 1.0000
9.250 0.7554 0.07441 0.06715 0.0211 0.0261 1.0000
9.500 0.7420 0.07796 0.07079 0.0229 0.0263 1.0000
9.750 0.7305 0.08166 0.07456 0.0237 0.0266 1.0000
10.250 0.6161 0.08415 0.07745 0.0253 0.0265 1.0000
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Polar data table (+)
Polar graphs
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