EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 50,000 Max Cl/Cd: 13.57 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e340-il-50000.txt Download as CSV file: xf-e340-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 340 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4709 0.11094 0.10515 0.0194 1.0000 0.2896
-9.000 -0.4664 0.10762 0.10189 0.0198 1.0000 0.3076
-8.750 -0.4709 0.10485 0.09923 0.0201 1.0000 0.3288
-8.500 -0.4602 0.10116 0.09562 0.0215 1.0000 0.3515
-8.250 -0.4591 0.09871 0.09325 0.0230 1.0000 0.3799
-8.000 -0.4382 0.09521 0.08980 0.0254 1.0000 0.4116
-7.750 -0.4446 0.09341 0.08813 0.0281 1.0000 0.4483
-7.500 -0.4070 0.08987 0.08461 0.0314 1.0000 0.4971
-6.500 -0.4202 0.07275 0.06797 0.0246 1.0000 0.4773
-6.250 -0.5070 0.06503 0.06051 0.0158 1.0000 0.4023
-6.000 -0.5617 0.05909 0.05427 0.0098 1.0000 0.3057
-5.750 -0.5949 0.05886 0.05415 0.0157 1.0000 0.3044
-5.500 -0.6124 0.05493 0.04890 0.0150 0.9949 0.1843
-5.250 -0.5573 0.04857 0.04129 0.0103 0.9749 0.1255
-5.000 -0.5038 0.04389 0.03573 0.0060 0.9562 0.1103
-4.750 -0.4505 0.04009 0.03131 0.0018 0.9366 0.1076
-4.500 -0.3920 0.03674 0.02737 -0.0028 0.9182 0.1087
-4.250 -0.3297 0.03366 0.02376 -0.0074 0.8994 0.1114
-4.000 0.0237 0.02721 0.02003 -0.0430 0.8901 1.0000
-3.750 0.0417 0.02723 0.01960 -0.0416 0.8583 1.0000
-3.500 0.0607 0.02727 0.01926 -0.0406 0.8320 1.0000
-3.250 0.0793 0.02735 0.01899 -0.0394 0.8108 1.0000
-3.000 0.0992 0.02744 0.01878 -0.0385 0.7920 1.0000
-2.750 0.1205 0.02756 0.01862 -0.0380 0.7749 1.0000
-2.500 0.1418 0.02770 0.01851 -0.0374 0.7594 1.0000
-2.250 0.1648 0.02789 0.01848 -0.0373 0.7444 1.0000
-2.000 0.1882 0.02813 0.01854 -0.0374 0.7307 1.0000
-1.750 0.2113 0.02843 0.01865 -0.0373 0.7182 1.0000
-1.500 0.2324 0.02873 0.01875 -0.0365 0.7075 1.0000
-1.250 0.2563 0.02911 0.01900 -0.0368 0.6958 1.0000
-1.000 0.2803 0.02959 0.01934 -0.0371 0.6854 1.0000
-0.750 0.3018 0.02997 0.01957 -0.0364 0.6765 1.0000
-0.500 0.3268 0.03061 0.02015 -0.0373 0.6661 1.0000
-0.250 0.3476 0.03103 0.02041 -0.0362 0.6586 1.0000
0.000 0.3732 0.03189 0.02127 -0.0376 0.6489 1.0000
0.250 0.3941 0.03239 0.02164 -0.0366 0.6421 1.0000
0.500 0.4184 0.03345 0.02271 -0.0380 0.6330 1.0000
0.750 0.4396 0.03407 0.02325 -0.0373 0.6262 1.0000
1.000 0.4621 0.03533 0.02454 -0.0385 0.6185 1.0000
1.250 0.4830 0.03626 0.02544 -0.0384 0.6114 1.0000
1.500 0.5032 0.03729 0.02645 -0.0381 0.6051 1.0000
1.750 0.5221 0.03899 0.02821 -0.0393 0.5978 1.0000
2.000 0.5416 0.03991 0.02910 -0.0384 0.5924 1.0000
2.250 0.5567 0.04190 0.03115 -0.0392 0.5860 1.0000
2.500 0.5700 0.04383 0.03314 -0.0394 0.5796 1.0000
2.750 0.5887 0.04476 0.03405 -0.0381 0.5746 1.0000
3.000 0.5923 0.04783 0.03721 -0.0387 0.5691 1.0000
3.250 0.5933 0.05070 0.04014 -0.0385 0.5640 1.0000
3.500 0.6021 0.05267 0.04213 -0.0375 0.5597 1.0000
3.750 0.6163 0.05425 0.04370 -0.0362 0.5557 1.0000
4.000 0.5952 0.05855 0.04805 -0.0351 0.5540 1.0000
4.250 0.5762 0.06219 0.05169 -0.0331 0.5536 1.0000
4.500 0.5642 0.06532 0.05482 -0.0311 0.5548 1.0000
4.750 0.5589 0.06809 0.05759 -0.0291 0.5565 1.0000
5.000 0.3497 0.07780 0.06724 -0.0206 0.7260 1.0000
5.250 0.3514 0.07884 0.06826 -0.0181 0.7109 1.0000
5.500 0.3534 0.08014 0.06955 -0.0159 0.6970 1.0000
5.750 0.3604 0.08186 0.07125 -0.0143 0.6838 1.0000
6.000 0.3788 0.08436 0.07377 -0.0143 0.6729 1.0000
6.500 0.3920 0.08754 0.07695 -0.0111 0.6461 1.0000
6.750 0.3969 0.08938 0.07878 -0.0096 0.6348 1.0000
7.000 0.4326 0.09324 0.08269 -0.0113 0.6245 1.0000
7.250 0.4205 0.09350 0.08294 -0.0078 0.6107 1.0000
7.500 0.4198 0.09515 0.08461 -0.0059 0.6002 1.0000
7.750 0.4541 0.09912 0.08864 -0.0072 0.5906 1.0000
8.000 0.4407 0.09937 0.08887 -0.0040 0.5771 1.0000
8.250 0.4415 0.10128 0.09079 -0.0025 0.5676 1.0000
8.500 0.4653 0.10444 0.09401 -0.0027 0.5576 1.0000
8.750 0.4542 0.10529 0.09486 -0.0003 0.5459 1.0000
9.000 0.4726 0.10863 0.09827 -0.0002 0.5380 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 340 AIRFOIL (e340-il)