EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 379 AIRFOIL (e379-il) Reynolds number: 100,000 Max Cl/Cd: 74.6 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e379-il-100000.txt Download as CSV file: xf-e379-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.0788 0.09222 0.08840 -0.0421 0.9097 0.0123
-7.000 -0.0648 0.09043 0.08654 -0.0439 0.8871 0.0127
-6.750 -0.0521 0.08893 0.08498 -0.0454 0.8670 0.0130
-6.500 -0.0374 0.08770 0.08370 -0.0473 0.8505 0.0133
-6.250 -0.0202 0.08683 0.08276 -0.0500 0.8358 0.0135
-6.000 0.0013 0.08631 0.08218 -0.0539 0.8223 0.0138
-5.750 0.0239 0.08547 0.08126 -0.0578 0.8098 0.0139
-5.500 0.0504 0.08492 0.08063 -0.0626 0.7981 0.0140
-5.250 0.0681 0.08145 0.07716 -0.0646 0.7884 0.0144
-5.000 0.0609 0.07366 0.06940 -0.0593 0.7821 0.0157
-4.750 0.0773 0.07072 0.06636 -0.0609 0.7724 0.0173
-4.500 0.0984 0.06844 0.06404 -0.0635 0.7639 0.0190
-4.250 0.1219 0.06622 0.06174 -0.0663 0.7563 0.0209
-4.000 0.1485 0.06413 0.05961 -0.0698 0.7477 0.0223
-3.750 0.1792 0.06245 0.05782 -0.0736 0.7408 0.0241
-3.500 0.2238 0.06250 0.05774 -0.0802 0.7321 0.0253
-3.250 0.2674 0.06255 0.05761 -0.0861 0.7245 0.0256
-2.750 0.3049 0.05473 0.04978 -0.0884 0.7119 0.0268
-2.500 0.3255 0.05163 0.04664 -0.0897 0.7054 0.0285
-2.250 0.3540 0.04956 0.04448 -0.0922 0.6995 0.0305
-2.000 0.3858 0.04783 0.04266 -0.0951 0.6927 0.0330
-1.750 0.4209 0.04656 0.04123 -0.0980 0.6872 0.0359
-1.500 0.4720 0.04805 0.04246 -0.1028 0.6798 0.0377
-1.250 0.4945 0.04438 0.03873 -0.1039 0.6756 0.0388
-1.000 0.5169 0.04167 0.03606 -0.1055 0.6688 0.0419
-0.750 0.5489 0.04031 0.03448 -0.1073 0.6637 0.0465
-0.250 0.6135 0.03787 0.03180 -0.1110 0.6520 0.0540
0.000 0.6176 0.01911 0.01334 -0.1054 0.6367 0.0635
0.250 0.6426 0.01783 0.01205 -0.1071 0.6309 0.0710
0.500 0.6734 0.01708 0.01114 -0.1084 0.6259 0.0786
0.750 0.7042 0.01611 0.00985 -0.1090 0.6223 0.0901
1.000 0.7333 0.01622 0.00991 -0.1107 0.6152 0.1020
1.250 0.7615 0.01526 0.00881 -0.1113 0.6112 0.1165
1.500 0.7904 0.01529 0.00866 -0.1120 0.6062 0.1392
1.750 0.8164 0.01492 0.00823 -0.1129 0.6003 0.1654
2.000 0.8428 0.01365 0.00682 -0.1130 0.5967 0.2096
2.250 0.8655 0.01345 0.00666 -0.1139 0.5903 0.2870
2.500 0.8927 0.01282 0.00602 -0.1140 0.5856 0.3314
2.750 0.9235 0.01238 0.00531 -0.1134 0.5825 0.3257
3.000 0.9511 0.01434 0.00713 -0.1137 0.5749 0.2134
3.250 0.9844 0.01435 0.00670 -0.1121 0.5712 0.0699
3.500 1.0099 0.01436 0.00650 -0.1115 0.5664 0.0532
3.750 1.0856 0.02924 0.02052 -0.1169 0.5706 0.0470
4.000 1.1111 0.02955 0.02072 -0.1170 0.5646 0.0531
4.250 1.1360 0.02961 0.02065 -0.1165 0.5593 0.0653
4.500 1.1643 0.02917 0.01998 -0.1156 0.5561 0.1082
4.750 1.1888 0.02961 0.02125 -0.1168 0.5480 1.0000
5.000 1.2150 0.02975 0.02116 -0.1160 0.5440 1.0000
5.250 1.2347 0.03103 0.02246 -0.1158 0.5368 1.0000
5.500 1.2596 0.03128 0.02262 -0.1151 0.5316 1.0000
5.750 1.2819 0.03198 0.02332 -0.1145 0.5256 1.0000
6.000 1.3040 0.03262 0.02399 -0.1140 0.5190 1.0000
6.250 1.3337 0.03206 0.02338 -0.1130 0.5158 1.0000
6.500 1.3592 0.03099 0.02225 -0.1115 0.5037 1.0000
6.750 1.3923 0.02648 0.01730 -0.1081 0.4783 1.0000
7.000 1.4179 0.02437 0.01497 -0.1061 0.4550 1.0000
7.250 1.4406 0.02285 0.01327 -0.1043 0.4263 1.0000
7.500 1.4633 0.02300 0.01354 -0.1036 0.4156 1.0000
7.750 1.4863 0.02317 0.01383 -0.1029 0.4060 1.0000
8.000 1.5089 0.02340 0.01423 -0.1022 0.3962 1.0000
8.250 1.5251 0.02337 0.01410 -0.1007 0.3531 1.0000
8.500 1.5428 0.02393 0.01464 -0.0996 0.3225 1.0000
8.750 1.5586 0.02477 0.01546 -0.0983 0.2911 1.0000
9.000 1.5622 0.02689 0.01822 -0.0956 0.2235 1.0000
9.250 1.5454 0.03053 0.02131 -0.0921 0.1484 1.0000
9.500 1.5305 0.03364 0.02426 -0.0888 0.1093 1.0000
9.750 1.5133 0.03731 0.02776 -0.0867 0.0771 1.0000
10.000 1.4915 0.04207 0.03229 -0.0856 0.0376 1.0000
10.250 1.4746 0.04678 0.03692 -0.0851 0.0221 1.0000
10.500 1.4664 0.05081 0.04109 -0.0847 0.0191 1.0000
10.750 1.4577 0.05500 0.04546 -0.0845 0.0168 1.0000
11.000 1.4507 0.05905 0.04971 -0.0844 0.0151 1.0000
11.250 1.4429 0.06331 0.05422 -0.0844 0.0141 1.0000
11.500 1.4359 0.06754 0.05865 -0.0845 0.0136 1.0000
11.750 1.4297 0.07176 0.06309 -0.0848 0.0135 1.0000
12.000 1.4224 0.07622 0.06778 -0.0852 0.0134 1.0000
12.250 1.4143 0.08104 0.07283 -0.0859 0.0135 1.0000
12.500 1.4060 0.08600 0.07801 -0.0867 0.0135 1.0000
12.750 1.3981 0.09104 0.08325 -0.0877 0.0135 1.0000
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Polar data table (+)
Polar graphs
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