EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 50,000 Max Cl/Cd: 15.78 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e338-il-50000.txt Download as CSV file: xf-e338-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 338 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3419 0.11374 0.10742 -0.0205 1.0000 0.1941
-9.250 -0.3261 0.11001 0.10373 -0.0194 1.0000 0.2050
-9.000 -0.3297 0.10700 0.10085 -0.0203 1.0000 0.2120
-8.750 -0.3325 0.10470 0.09864 -0.0205 1.0000 0.2240
-8.500 -0.3173 0.10063 0.09464 -0.0193 1.0000 0.2359
-8.250 -0.3182 0.09767 0.09180 -0.0191 1.0000 0.2476
-8.000 -0.3491 0.09673 0.09107 -0.0203 1.0000 0.2584
-7.750 -0.3441 0.09365 0.08811 -0.0188 1.0000 0.2747
-7.500 -0.3458 0.09102 0.08561 -0.0172 1.0000 0.2912
-7.250 -0.3130 0.08694 0.08156 -0.0139 1.0000 0.3201
-6.750 -0.3222 0.08300 0.07798 -0.0081 1.0000 0.3728
-6.500 -0.2831 0.07980 0.07483 -0.0032 1.0000 0.4349
-6.250 -0.2461 0.07717 0.07225 0.0023 1.0000 0.5173
-6.000 -0.2137 0.07511 0.07029 0.0073 1.0000 0.6068
-5.750 -0.1255 0.06960 0.06473 0.0053 1.0000 0.7259
-4.750 -0.1945 0.06365 0.05941 -0.0029 0.9481 0.6249
-4.500 -0.2555 0.05903 0.05484 -0.0113 0.9190 0.5431
-4.250 -0.3021 0.05354 0.04881 -0.0266 0.8913 0.4246
-4.000 -0.2319 0.04681 0.03958 -0.0433 0.8759 0.1710
-3.750 -0.1904 0.04367 0.03561 -0.0444 0.8631 0.1380
-3.500 -0.1422 0.04061 0.03182 -0.0463 0.8528 0.1221
-3.250 -0.1115 0.03857 0.02935 -0.0459 0.8386 0.1163
-3.000 -0.0796 0.03696 0.02736 -0.0458 0.8251 0.1161
-2.750 0.2753 0.02468 0.01730 -0.0889 0.8218 1.0000
-2.500 0.2964 0.02497 0.01704 -0.0877 0.8055 1.0000
-2.250 0.3165 0.02532 0.01699 -0.0866 0.7901 1.0000
-2.000 0.3366 0.02574 0.01709 -0.0857 0.7759 1.0000
-1.750 0.3563 0.02619 0.01726 -0.0847 0.7629 1.0000
-1.500 0.3765 0.02660 0.01739 -0.0835 0.7514 1.0000
-1.250 0.3954 0.02712 0.01769 -0.0824 0.7399 1.0000
-1.000 0.4124 0.02782 0.01824 -0.0813 0.7288 1.0000
-0.750 0.4330 0.02828 0.01846 -0.0801 0.7197 1.0000
-0.500 0.4487 0.02912 0.01919 -0.0789 0.7091 1.0000
-0.250 0.4664 0.02986 0.01979 -0.0778 0.7003 1.0000
0.000 0.4832 0.03068 0.02049 -0.0766 0.6915 1.0000
0.250 0.4986 0.03164 0.02136 -0.0753 0.6832 1.0000
0.500 0.5141 0.03258 0.02220 -0.0740 0.6751 1.0000
0.750 0.5284 0.03367 0.02321 -0.0726 0.6677 1.0000
1.000 0.5389 0.03501 0.02451 -0.0711 0.6599 1.0000
1.250 0.5592 0.03570 0.02508 -0.0698 0.6539 1.0000
1.500 0.5556 0.03799 0.02741 -0.0675 0.6458 1.0000
1.750 0.5744 0.03882 0.02816 -0.0662 0.6399 1.0000
2.000 0.5682 0.04124 0.03060 -0.0635 0.6335 1.0000
2.250 0.5642 0.04341 0.03275 -0.0607 0.6272 1.0000
2.500 0.5911 0.04392 0.03317 -0.0600 0.6221 1.0000
2.750 0.5512 0.04799 0.03729 -0.0546 0.6174 1.0000
3.000 0.5181 0.05126 0.04056 -0.0493 0.6137 1.0000
3.250 0.4859 0.05401 0.04328 -0.0435 0.6119 1.0000
3.500 0.4628 0.05652 0.04576 -0.0390 0.6111 1.0000
3.750 0.4423 0.05902 0.04823 -0.0351 0.6118 1.0000
4.000 0.4254 0.06151 0.05068 -0.0319 0.6145 1.0000
4.250 0.4211 0.06390 0.05304 -0.0302 0.6183 1.0000
4.500 0.4340 0.06626 0.05536 -0.0300 0.6215 1.0000
5.250 0.3039 0.07486 0.06403 -0.0207 0.7415 1.0000
5.500 0.3136 0.07645 0.06557 -0.0196 0.7289 1.0000
5.750 0.3421 0.07955 0.06862 -0.0211 0.7201 1.0000
6.000 0.3505 0.08079 0.06982 -0.0199 0.7063 1.0000
6.250 0.3545 0.08205 0.07105 -0.0182 0.6936 1.0000
6.500 0.3674 0.08415 0.07313 -0.0178 0.6830 1.0000
6.750 0.3958 0.08717 0.07614 -0.0191 0.6720 1.0000
7.000 0.3935 0.08801 0.07696 -0.0170 0.6593 1.0000
7.250 0.4027 0.09000 0.07895 -0.0163 0.6488 1.0000
7.500 0.4351 0.09360 0.08256 -0.0180 0.6386 1.0000
7.750 0.4290 0.09420 0.08315 -0.0158 0.6262 1.0000
8.000 0.4372 0.09634 0.08530 -0.0152 0.6160 1.0000
8.250 0.4673 0.09985 0.08884 -0.0166 0.6059 1.0000
8.500 0.4614 0.10070 0.08970 -0.0148 0.5936 1.0000
8.750 0.4731 0.10338 0.09241 -0.0148 0.5854 1.0000
9.000 0.4954 0.10629 0.09536 -0.0153 0.5737 1.0000
9.250 0.4905 0.10751 0.09659 -0.0140 0.5621 1.0000
9.500 0.5171 0.11162 0.10075 -0.0152 0.5554 1.0000
9.750 0.5172 0.11280 0.10196 -0.0142 0.5426 1.0000
10.000 0.5178 0.11475 0.10394 -0.0137 0.5325 1.0000
10.250 0.5502 0.11921 0.10851 -0.0151 0.5241 1.0000
10.500 0.5383 0.11981 0.10913 -0.0138 0.5127 1.0000
10.750 0.5528 0.12320 0.11257 -0.0143 0.5053 1.0000
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Polar data table (+)
Polar graphs
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