EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 200,000 Max Cl/Cd: 117.83 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e379-il-200000.txt Download as CSV file: xf-e379-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 379 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1487 0.09831 0.09510 -0.0235 0.8365 0.0035
-7.750 -0.1412 0.09624 0.09294 -0.0239 0.8144 0.0036
-7.500 -0.1337 0.09432 0.09093 -0.0243 0.7967 0.0036
-7.250 -0.1246 0.09233 0.08887 -0.0252 0.7815 0.0036
-7.000 -0.1130 0.09008 0.08655 -0.0267 0.7677 0.0037
-6.750 -0.1003 0.08785 0.08426 -0.0283 0.7555 0.0038
-6.500 -0.0862 0.08554 0.08190 -0.0303 0.7439 0.0039
-6.250 -0.0709 0.08319 0.07949 -0.0324 0.7334 0.0040
-6.000 -0.0545 0.08079 0.07704 -0.0348 0.7240 0.0042
-5.750 -0.0371 0.07846 0.07464 -0.0372 0.7157 0.0043
-5.500 -0.0180 0.07605 0.07220 -0.0399 0.7065 0.0045
-5.250 0.0023 0.07367 0.06976 -0.0427 0.6990 0.0046
-5.000 0.0250 0.07134 0.06738 -0.0458 0.6914 0.0050
-4.750 0.0515 0.06939 0.06538 -0.0495 0.6841 0.0053
-4.500 0.0862 0.06861 0.06443 -0.0549 0.6770 0.0057
-4.250 0.1281 0.06850 0.06422 -0.0620 0.6693 0.0059
-4.000 0.1548 0.06536 0.06101 -0.0654 0.6636 0.0060
-3.750 0.1603 0.05945 0.05515 -0.0643 0.6581 0.0065
-3.500 0.1809 0.05626 0.05191 -0.0663 0.6521 0.0073
-3.250 0.2086 0.05379 0.04936 -0.0694 0.6466 0.0088
-3.000 0.2396 0.05145 0.04696 -0.0730 0.6405 0.0095
-2.750 0.2711 0.04926 0.04465 -0.0763 0.6358 0.0101
0.000 0.6364 0.03014 0.02426 -0.1037 0.5808 0.0214
0.250 0.6710 0.02934 0.02336 -0.1049 0.5756 0.0242
0.500 0.7099 0.03004 0.02378 -0.1054 0.5714 0.0256
0.750 0.7356 0.02681 0.02046 -0.1070 0.5677 0.0279
1.000 0.7650 0.02557 0.01911 -0.1078 0.5625 0.0333
1.250 0.8026 0.02675 0.01995 -0.1075 0.5582 0.0379
1.500 0.8268 0.02374 0.01691 -0.1089 0.5548 0.0450
1.750 0.8597 0.02344 0.01646 -0.1090 0.5499 0.0513
2.000 0.8871 0.02215 0.01508 -0.1095 0.5457 0.0578
2.250 0.9169 0.02146 0.01415 -0.1095 0.5423 0.0665
2.500 0.9477 0.02185 0.01446 -0.1092 0.5371 0.0876
2.750 0.9748 0.02019 0.01277 -0.1097 0.5329 0.1026
3.000 1.0032 0.01964 0.01201 -0.1095 0.5295 0.1274
3.250 1.0307 0.01898 0.01135 -0.1096 0.5249 0.1558
3.500 1.0632 0.01841 0.01041 -0.1083 0.5208 0.0484
3.750 0.9497 0.00806 0.00085 -0.1102 0.5264 0.0255
4.000 1.1188 0.01726 0.00890 -0.1073 0.5133 0.0250
4.250 1.1457 0.01693 0.00853 -0.1071 0.5083 0.0238
4.500 1.1732 0.01679 0.00821 -0.1068 0.5042 0.0459
4.750 1.2060 0.01602 0.00840 -0.1081 0.4997 1.0000
5.000 1.2318 0.01625 0.00858 -0.1079 0.4943 1.0000
5.250 1.2581 0.01639 0.00860 -0.1076 0.4900 1.0000
5.500 1.2835 0.01666 0.00889 -0.1075 0.4844 1.0000
5.750 1.3066 0.01503 0.00691 -0.1058 0.4497 1.0000
6.000 1.3308 0.01479 0.00669 -0.1052 0.4283 1.0000
6.250 1.3541 0.01473 0.00644 -0.1046 0.3973 1.0000
6.500 1.3763 0.01501 0.00648 -0.1041 0.3569 1.0000
6.750 1.3997 0.01538 0.00677 -0.1037 0.3357 1.0000
7.000 1.4227 0.01581 0.00714 -0.1033 0.3154 1.0000
7.250 1.4455 0.01628 0.00759 -0.1028 0.2959 1.0000
7.500 1.4683 0.01674 0.00808 -0.1024 0.2806 1.0000
7.750 1.4772 0.01880 0.00949 -0.1010 0.1908 1.0000
8.000 1.4708 0.02241 0.01215 -0.0983 0.0711 1.0000
8.250 1.4700 0.02495 0.01427 -0.0958 0.0125 1.0000
8.500 1.4828 0.02602 0.01530 -0.0943 0.0111 1.0000
8.750 1.4987 0.02674 0.01623 -0.0931 0.0098 1.0000
9.000 1.5083 0.02779 0.01745 -0.0912 0.0098 1.0000
9.250 1.5143 0.02908 0.01892 -0.0892 0.0099 1.0000
9.750 1.5093 0.03440 0.02574 -0.0853 0.0084 1.0000
10.000 1.5075 0.03733 0.02897 -0.0842 0.0091 1.0000
10.250 1.5065 0.04029 0.03217 -0.0835 0.0098 1.0000
10.500 1.5042 0.04346 0.03553 -0.0829 0.0100 1.0000
10.750 1.4995 0.04708 0.03939 -0.0826 0.0108 1.0000
11.000 1.4940 0.05080 0.04328 -0.0824 0.0110 1.0000
11.250 1.4859 0.05496 0.04762 -0.0823 0.0116 1.0000
11.500 1.4784 0.05907 0.05188 -0.0822 0.0118 1.0000
11.750 1.4712 0.06315 0.05610 -0.0821 0.0122 1.0000
12.000 1.4642 0.06721 0.06028 -0.0819 0.0126 1.0000
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Polar data table (+)
Polar graphs
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