EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 500,000 Max Cl/Cd: 127.97 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e379-il-500000.txt Download as CSV file: xf-e379-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-2.750 0.2705 0.04624 0.04235 -0.0750 0.5656 0.0032
-2.500 0.3026 0.04400 0.04005 -0.0783 0.5611 0.0035
-2.250 0.3353 0.04188 0.03783 -0.0814 0.5570 0.0036
-2.000 0.3686 0.03981 0.03569 -0.0844 0.5527 0.0036
-1.750 0.4022 0.03780 0.03361 -0.0873 0.5482 0.0036
-1.500 0.4357 0.03590 0.03161 -0.0900 0.5441 0.0036
-1.250 0.4695 0.03407 0.02968 -0.0924 0.5401 0.0036
-1.000 0.5032 0.03230 0.02781 -0.0947 0.5357 0.0037
-0.750 0.5368 0.03062 0.02603 -0.0968 0.5318 0.0037
-0.500 0.5700 0.02907 0.02434 -0.0986 0.5283 0.0038
-0.250 0.6034 0.02752 0.02272 -0.1003 0.5242 0.0039
0.000 0.6364 0.02607 0.02116 -0.1017 0.5202 0.0040
0.250 0.6690 0.02474 0.01968 -0.1030 0.5166 0.0041
0.500 0.7014 0.02344 0.01828 -0.1040 0.5128 0.0043
0.750 0.7338 0.02215 0.01683 -0.1049 0.5089 0.0040
1.000 0.7656 0.02101 0.01556 -0.1056 0.5054 0.0043
1.250 0.7969 0.02001 0.01439 -0.1060 0.5019 0.0047
1.500 0.8287 0.01911 0.01340 -0.1063 0.4980 0.0053
1.750 0.8610 0.01821 0.01235 -0.1063 0.4941 0.0063
2.000 0.8890 0.01709 0.01111 -0.1069 0.4905 0.0106
2.250 0.9196 0.01688 0.01077 -0.1064 0.4869 0.0138
2.500 0.9497 0.01543 0.00917 -0.1067 0.4832 0.0160
2.750 0.9783 0.01476 0.00846 -0.1067 0.4796 0.0237
3.000 1.0067 0.01405 0.00757 -0.1066 0.4761 0.0326
3.250 1.0352 0.01342 0.00685 -0.1065 0.4723 0.0434
3.500 1.0634 0.01296 0.00626 -0.1063 0.4682 0.0648
3.750 1.0909 0.01245 0.00566 -0.1061 0.4642 0.0800
4.500 1.1736 0.01088 0.00367 -0.1045 0.4518 0.0120
4.750 1.2000 0.01065 0.00381 -0.1044 0.4473 0.3834
5.000 1.2330 0.00985 0.00383 -0.1058 0.4401 1.0000
5.250 1.2579 0.00983 0.00351 -0.1055 0.3901 1.0000
5.500 1.2831 0.01011 0.00363 -0.1053 0.3676 1.0000
5.750 1.3087 0.01035 0.00380 -0.1052 0.3515 1.0000
6.000 1.3024 0.01586 0.00714 -0.1030 0.0065 1.0000
6.250 1.3230 0.01673 0.00781 -0.1022 0.0052 1.0000
6.500 1.3499 0.01655 0.00773 -0.1022 0.0041 1.0000
6.750 1.3732 0.01692 0.00811 -0.1018 0.0042 1.0000
7.000 1.3963 0.01730 0.00853 -0.1014 0.0043 1.0000
7.250 1.4189 0.01774 0.00902 -0.1009 0.0047 1.0000
7.500 1.4410 0.01820 0.00958 -0.1003 0.0051 1.0000
7.750 1.4637 0.01856 0.01004 -0.0999 0.0056 1.0000
8.000 1.4860 0.01896 0.01045 -0.0993 0.0060 1.0000
8.250 1.5071 0.01947 0.01100 -0.0985 0.0064 1.0000
8.500 1.5273 0.02005 0.01166 -0.0977 0.0067 1.0000
8.750 1.5456 0.02077 0.01255 -0.0966 0.0072 1.0000
12.250 1.4798 0.06450 0.05887 -0.0740 0.0024 1.0000
12.500 1.4781 0.06799 0.06254 -0.0747 0.0022 1.0000
12.750 1.4801 0.07120 0.06591 -0.0745 0.0021 1.0000
13.000 1.3321 0.08016 0.07538 -0.0673 0.0025 1.0000
13.250 1.3187 0.08572 0.08115 -0.0690 0.0024 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 379 AIRFOIL (e379-il)