EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 376 AIRFOIL (e376-il) Reynolds number: 500,000 Max Cl/Cd: 129.57 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e376-il-500000-n5.txt Download as CSV file: xf-e376-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4970 0.18628 0.18396 0.0302 1.0000 0.0023
-15.500 -0.4887 0.18325 0.18094 0.0285 1.0000 0.0024
-15.250 -0.4803 0.18028 0.17797 0.0269 1.0000 0.0024
-15.000 -0.4717 0.17727 0.17496 0.0252 1.0000 0.0025
-14.750 -0.4630 0.17429 0.17197 0.0235 1.0000 0.0027
-14.500 -0.4543 0.17127 0.16896 0.0219 1.0000 0.0028
-14.250 -0.4456 0.16825 0.16594 0.0203 1.0000 0.0030
-14.000 -0.4371 0.16528 0.16297 0.0188 1.0000 0.0031
-13.750 -0.4285 0.16224 0.15994 0.0173 1.0000 0.0034
-13.500 -0.4198 0.15930 0.15700 0.0157 1.0000 0.0035
-13.250 -0.4110 0.15634 0.15405 0.0142 1.0000 0.0037
-13.000 -0.4022 0.15338 0.15109 0.0128 1.0000 0.0038
-12.750 -0.3935 0.15047 0.14820 0.0113 1.0000 0.0038
-12.500 -0.3848 0.14754 0.14527 0.0099 1.0000 0.0038
-12.250 -0.3761 0.14470 0.14244 0.0084 1.0000 0.0038
-6.750 -0.1422 0.08751 0.08426 -0.0260 0.6580 0.0040
-6.500 -0.1266 0.08504 0.08175 -0.0283 0.6489 0.0040
-6.250 -0.1101 0.08258 0.07924 -0.0308 0.6396 0.0041
-6.000 -0.0924 0.08007 0.07671 -0.0334 0.6315 0.0041
-5.750 -0.0731 0.07753 0.07412 -0.0363 0.6234 0.0041
-5.500 -0.0522 0.07497 0.07152 -0.0395 0.6148 0.0041
-5.250 -0.0298 0.07242 0.06892 -0.0429 0.6090 0.0041
-4.750 0.0094 0.06643 0.06287 -0.0481 0.5956 0.0044
-4.500 0.0333 0.06396 0.06035 -0.0513 0.5891 0.0047
-4.250 0.0588 0.06153 0.05785 -0.0546 0.5832 0.0054
-4.000 0.0877 0.05912 0.05540 -0.0583 0.5776 0.0062
-3.750 0.1170 0.05673 0.05294 -0.0620 0.5712 0.0063
-3.500 0.1472 0.05437 0.05053 -0.0657 0.5663 0.0064
-3.250 0.1785 0.05202 0.04812 -0.0695 0.5609 0.0064
-3.000 0.2107 0.04973 0.04575 -0.0732 0.5558 0.0064
-2.750 0.2438 0.04748 0.04342 -0.0769 0.5509 0.0065
-2.500 0.2777 0.04525 0.04113 -0.0805 0.5457 0.0065
-2.250 0.3121 0.04309 0.03887 -0.0840 0.5409 0.0065
-2.000 0.3469 0.04096 0.03666 -0.0874 0.5366 0.0065
-1.750 0.3815 0.03885 0.03447 -0.0905 0.5318 0.0065
-1.500 0.4135 0.03629 0.03183 -0.0932 0.5273 0.0066
-1.250 0.4432 0.03400 0.02947 -0.0955 0.5231 0.0068
-1.000 0.4763 0.03217 0.02757 -0.0979 0.5187 0.0071
-0.750 0.5103 0.03045 0.02576 -0.1002 0.5145 0.0075
-0.500 0.5446 0.02880 0.02400 -0.1023 0.5104 0.0080
-0.250 0.5794 0.02718 0.02229 -0.1043 0.5060 0.0087
0.000 0.6166 0.02589 0.02087 -0.1060 0.5018 0.0096
0.250 0.6516 0.02441 0.01926 -0.1075 0.4980 0.0097
0.500 0.6843 0.02222 0.01695 -0.1091 0.4942 0.0071
0.750 0.7174 0.02088 0.01549 -0.1101 0.4898 0.0077
1.000 0.7506 0.02065 0.01515 -0.1104 0.4855 0.0149
1.500 0.8139 0.01741 0.01163 -0.1120 0.4778 0.0111
1.750 0.8472 0.01597 0.00999 -0.1123 0.4735 0.0098
2.000 0.8791 0.01451 0.00829 -0.1125 0.4696 0.0098
2.250 0.9131 0.01145 0.00473 -0.1126 0.4663 0.0110
2.500 0.9408 0.01088 0.00401 -0.1124 0.4619 0.0145
2.750 0.9680 0.01022 0.00314 -0.1122 0.4575 0.0171
3.000 0.9948 0.01015 0.00302 -0.1119 0.4534 0.0211
3.250 1.0217 0.00993 0.00274 -0.1117 0.4488 0.0246
3.500 1.0486 0.00993 0.00272 -0.1115 0.4440 0.0313
3.750 1.0753 0.00994 0.00273 -0.1113 0.4393 0.0392
4.000 1.1021 0.00997 0.00276 -0.1111 0.4334 0.0478
4.250 1.1286 0.01005 0.00281 -0.1109 0.4268 0.0565
4.500 1.1554 0.01010 0.00289 -0.1107 0.4202 0.0661
4.750 1.1818 0.01020 0.00300 -0.1105 0.4140 0.0784
5.000 1.2083 0.01030 0.00312 -0.1104 0.4076 0.0896
5.250 1.2346 0.01043 0.00330 -0.1102 0.3994 0.1041
5.500 1.2609 0.01055 0.00344 -0.1100 0.3909 0.1176
5.750 1.2869 0.01071 0.00361 -0.1098 0.3829 0.1319
6.000 1.3130 0.01085 0.00380 -0.1096 0.3738 0.1491
6.250 1.3388 0.01102 0.00400 -0.1094 0.3640 0.1655
6.500 1.3645 0.01123 0.00428 -0.1091 0.3525 0.1859
6.750 1.3899 0.01146 0.00454 -0.1089 0.3393 0.2194
7.000 1.4162 0.01093 0.00486 -0.1091 0.3238 1.0000
7.250 1.4407 0.01130 0.00517 -0.1087 0.3043 1.0000
7.500 1.4644 0.01179 0.00556 -0.1083 0.2783 1.0000
7.750 1.4869 0.01244 0.00610 -0.1079 0.2464 1.0000
8.000 1.5084 0.01323 0.00673 -0.1073 0.2110 1.0000
8.250 1.5294 0.01408 0.00743 -0.1067 0.1794 1.0000
8.500 1.5497 0.01496 0.00818 -0.1061 0.1497 1.0000
9.000 1.5894 0.01671 0.00977 -0.1046 0.1008 1.0000
9.250 1.6085 0.01758 0.01059 -0.1038 0.0827 1.0000
9.500 1.6256 0.01864 0.01155 -0.1028 0.0622 1.0000
9.750 1.6420 0.01970 0.01255 -0.1017 0.0449 1.0000
10.000 1.6564 0.02087 0.01365 -0.1004 0.0308 1.0000
10.250 1.6688 0.02213 0.01486 -0.0989 0.0185 1.0000
10.500 1.6788 0.02347 0.01621 -0.0971 0.0100 1.0000
10.750 1.6875 0.02478 0.01756 -0.0951 0.0058 1.0000
11.000 1.6907 0.02618 0.01903 -0.0924 0.0035 1.0000
11.250 1.6896 0.02782 0.02077 -0.0895 0.0024 1.0000
11.500 1.6890 0.02971 0.02280 -0.0874 0.0019 1.0000
11.750 1.6873 0.03203 0.02525 -0.0858 0.0015 1.0000
12.000 1.6818 0.03507 0.02846 -0.0847 0.0012 1.0000
12.250 1.6801 0.03792 0.03146 -0.0840 0.0011 1.0000
12.500 1.6774 0.04104 0.03474 -0.0836 0.0011 1.0000
12.750 1.6738 0.04441 0.03827 -0.0834 0.0010 1.0000
13.000 1.6680 0.04819 0.04220 -0.0834 0.0010 1.0000
13.250 1.6620 0.05206 0.04622 -0.0835 0.0009 1.0000
13.500 1.6546 0.05623 0.05054 -0.0838 0.0009 1.0000
13.750 1.6470 0.06049 0.05496 -0.0842 0.0009 1.0000
14.000 1.6389 0.06494 0.05955 -0.0849 0.0009 1.0000
14.250 1.6288 0.06982 0.06461 -0.0857 0.0009 1.0000
14.500 1.6194 0.07482 0.06976 -0.0867 0.0008 1.0000
14.750 1.6099 0.07999 0.07508 -0.0880 0.0008 1.0000
15.000 1.6001 0.08539 0.08063 -0.0894 0.0008 1.0000
15.250 1.5905 0.09092 0.08630 -0.0910 0.0008 1.0000
15.500 1.5804 0.09667 0.09220 -0.0928 0.0008 1.0000
15.750 1.5708 0.10246 0.09815 -0.0947 0.0008 1.0000
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Polar data table (+)
Polar graphs
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