EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 100,000 Max Cl/Cd: 105.59 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e376-il-100000.txt Download as CSV file: xf-e376-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 376 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.1892 0.09558 0.09166 -0.0184 1.0000 0.0186
-6.750 -0.1953 0.09494 0.09120 -0.0168 1.0000 0.0190
-6.500 -0.1867 0.09340 0.08971 -0.0194 0.9910 0.0195
-6.250 -0.1423 0.08919 0.08546 -0.0295 0.9773 0.0210
-6.000 -0.0870 0.08620 0.08239 -0.0422 0.9636 0.0222
-5.750 -0.0203 0.08601 0.08208 -0.0585 0.9460 0.0228
-5.250 0.0353 0.07578 0.07179 -0.0670 0.9146 0.0235
-5.000 0.0510 0.07117 0.06713 -0.0677 0.8982 0.0243
-4.750 0.0700 0.06837 0.06426 -0.0695 0.8797 0.0251
-4.500 0.0919 0.06593 0.06175 -0.0719 0.8634 0.0262
-4.250 0.1148 0.06371 0.05942 -0.0743 0.8483 0.0272
-4.000 0.1392 0.06157 0.05720 -0.0770 0.8347 0.0285
-3.750 0.1653 0.05954 0.05507 -0.0798 0.8223 0.0298
-3.500 0.1948 0.05775 0.05316 -0.0831 0.8105 0.0314
-3.250 0.2435 0.05847 0.05367 -0.0899 0.7987 0.0331
-3.000 0.2882 0.05829 0.05331 -0.0959 0.7871 0.0337
-2.750 0.2911 0.05215 0.04724 -0.0940 0.7785 0.0348
-2.500 0.3132 0.04930 0.04429 -0.0952 0.7701 0.0366
-2.250 0.3430 0.04726 0.04217 -0.0980 0.7603 0.0389
-2.000 0.3759 0.04553 0.04030 -0.1010 0.7521 0.0418
-1.750 0.4199 0.04541 0.03997 -0.1051 0.7432 0.0449
-1.500 0.4705 0.04676 0.04104 -0.1099 0.7340 0.0458
-1.250 0.4821 0.04118 0.03552 -0.1099 0.7279 0.0472
-1.000 0.5090 0.03905 0.03333 -0.1116 0.7196 0.0499
-0.750 0.5410 0.03766 0.03176 -0.1133 0.7132 0.0536
-0.500 0.5866 0.03889 0.03275 -0.1164 0.7045 0.0579
-0.250 0.6123 0.03591 0.02969 -0.1175 0.6989 0.0595
0.000 0.6392 0.03408 0.02785 -0.1190 0.6909 0.0637
0.250 0.6403 0.01490 0.00897 -0.1124 0.6721 0.0735
0.500 0.6749 0.01523 0.00912 -0.1138 0.6651 0.0828
0.750 0.7018 0.01349 0.00733 -0.1152 0.6593 0.0869
1.000 0.7352 0.01357 0.00718 -0.1160 0.6537 0.0964
1.250 0.7622 0.01251 0.00611 -0.1173 0.6472 0.1048
1.500 0.7916 0.01181 0.00524 -0.1177 0.6422 0.1145
1.750 0.8208 0.01173 0.00510 -0.1188 0.6353 0.1260
2.000 0.8493 0.01130 0.00453 -0.1191 0.6298 0.1403
2.250 0.8771 0.01113 0.00426 -0.1196 0.6239 0.1622
2.500 0.9038 0.01080 0.00387 -0.1201 0.6176 0.2016
2.750 0.9674 0.02654 0.01900 -0.1267 0.6218 0.2289
3.000 0.9562 0.00995 0.00292 -0.1208 0.6058 0.3156
3.250 0.9847 0.00967 0.00247 -0.1205 0.6007 0.3228
3.500 1.0178 0.01088 0.00330 -0.1192 0.5944 0.1195
3.750 1.0438 0.01073 0.00305 -0.1189 0.5883 0.1285
4.000 1.0715 0.01049 0.00256 -0.1184 0.5836 0.1600
4.250 1.0952 0.01104 0.00311 -0.1184 0.5759 0.1825
4.500 1.1205 0.01067 0.00259 -0.1173 0.5713 0.1924
4.750 1.1417 0.01139 0.00340 -0.1171 0.5627 0.2155
5.000 1.1664 0.01116 0.00314 -0.1161 0.5577 0.2335
5.250 1.1878 0.01194 0.00401 -0.1159 0.5492 0.2632
5.500 1.2153 0.01151 0.00422 -0.1153 0.5439 1.0000
5.750 1.2367 0.01250 0.00519 -0.1148 0.5352 1.0000
6.000 1.2624 0.01242 0.00498 -0.1137 0.5294 1.0000
6.250 1.2830 0.01343 0.00609 -0.1132 0.5202 1.0000
6.500 1.3109 0.01301 0.00567 -0.1121 0.5143 1.0000
6.750 1.3887 0.02815 0.02033 -0.1187 0.5157 1.0000
7.000 1.4110 0.02864 0.02096 -0.1179 0.5059 1.0000
7.250 1.4384 0.02822 0.02049 -0.1167 0.4987 1.0000
7.500 1.4610 0.02848 0.02091 -0.1158 0.4878 1.0000
7.750 1.4838 0.02864 0.02123 -0.1148 0.4767 1.0000
8.000 1.5083 0.02845 0.02126 -0.1137 0.4657 1.0000
8.250 1.5338 0.02800 0.02090 -0.1125 0.4541 1.0000
8.500 1.5583 0.02757 0.02060 -0.1112 0.4408 1.0000
8.750 1.5810 0.02725 0.02047 -0.1099 0.4251 1.0000
9.000 1.6032 0.02688 0.02029 -0.1085 0.4072 1.0000
9.250 1.6251 0.02622 0.01980 -0.1068 0.3856 1.0000
9.500 1.6408 0.02589 0.01967 -0.1047 0.3508 1.0000
9.750 1.6522 0.02621 0.01992 -0.1024 0.3037 1.0000
10.000 1.6561 0.02769 0.02116 -0.0999 0.2452 1.0000
10.250 1.6505 0.03023 0.02329 -0.0970 0.1899 1.0000
10.500 1.6397 0.03314 0.02594 -0.0938 0.1476 1.0000
10.750 1.6223 0.03633 0.02893 -0.0903 0.1174 1.0000
11.000 1.6027 0.04036 0.03280 -0.0882 0.0920 1.0000
11.250 1.5825 0.04514 0.03742 -0.0872 0.0737 1.0000
11.500 1.5626 0.05040 0.04260 -0.0867 0.0587 1.0000
11.750 1.5446 0.05570 0.04782 -0.0867 0.0511 1.0000
12.000 1.5326 0.06044 0.05268 -0.0865 0.0440 1.0000
12.250 1.5186 0.06539 0.05763 -0.0864 0.0406 1.0000
12.500 1.5135 0.06926 0.06164 -0.0857 0.0370 1.0000
12.750 1.5106 0.07281 0.06529 -0.0849 0.0341 1.0000
13.000 1.5098 0.07607 0.06860 -0.0837 0.0317 1.0000
13.250 1.5255 0.07755 0.07009 -0.0794 0.0294 1.0000
13.500 1.5378 0.08023 0.07305 -0.0772 0.0284 1.0000
13.750 1.5446 0.08391 0.07704 -0.0758 0.0278 1.0000
14.000 1.5425 0.08849 0.08192 -0.0757 0.0273 1.0000
14.250 1.5358 0.09356 0.08730 -0.0764 0.0269 1.0000
14.500 1.5256 0.09903 0.09306 -0.0777 0.0265 1.0000
14.750 1.5135 0.10490 0.09921 -0.0796 0.0263 1.0000
15.000 1.4997 0.11126 0.10585 -0.0821 0.0263 1.0000
15.250 1.4845 0.11805 0.11290 -0.0853 0.0264 1.0000
15.500 1.4684 0.12533 0.12043 -0.0891 0.0266 1.0000
15.750 1.4520 0.13306 0.12839 -0.0935 0.0269 1.0000
16.000 1.4353 0.14135 0.13689 -0.0985 0.0276 1.0000
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Polar data table (+)
Polar graphs
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