EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 50,000 Max Cl/Cd: 17.7 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e326-il-50000.txt Download as CSV file: xf-e326-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5291 0.14840 0.14157 0.0075 1.0000 0.1791
-11.750 -0.4915 0.14107 0.13421 0.0102 1.0000 0.1889
-11.500 -0.5155 0.14037 0.13363 0.0065 1.0000 0.1944
-11.250 -0.4841 0.13411 0.12734 0.0086 1.0000 0.2047
-11.000 -0.5004 0.13191 0.12527 0.0059 1.0000 0.2111
-10.750 -0.4825 0.12766 0.12100 0.0068 1.0000 0.2230
-10.500 -0.4731 0.12355 0.11694 0.0068 1.0000 0.2320
-10.250 -0.5022 0.12248 0.11601 0.0038 1.0000 0.2412
-10.000 -0.4897 0.11829 0.11186 0.0047 1.0000 0.2563
-9.750 -0.4795 0.11445 0.10806 0.0054 1.0000 0.2712
-9.500 -0.4806 0.11133 0.10502 0.0055 1.0000 0.2871
-9.250 -0.4656 0.10713 0.10086 0.0068 1.0000 0.3051
-9.000 -0.4457 0.10347 0.09723 0.0084 1.0000 0.3270
-8.750 -0.4664 0.10182 0.09571 0.0089 1.0000 0.3500
-8.500 -0.4295 0.09755 0.09142 0.0119 1.0000 0.3850
-8.250 -0.4262 0.09559 0.08953 0.0148 1.0000 0.4255
-8.000 -0.3940 0.09165 0.08561 0.0170 1.0000 0.4641
-6.750 -0.4405 0.07257 0.06711 0.0133 1.0000 0.4450
-6.500 -0.5050 0.06663 0.06141 0.0097 1.0000 0.3995
-6.250 -0.5686 0.06089 0.05559 0.0064 1.0000 0.3374
-6.000 -0.5780 0.05301 0.04607 0.0015 1.0000 0.1577
-5.750 -0.5705 0.04957 0.04199 0.0049 1.0000 0.1295
-5.500 -0.5649 0.04719 0.03905 0.0089 1.0000 0.1165
-5.250 -0.5579 0.04448 0.03629 0.0118 1.0000 0.1138
-5.000 -0.5561 0.04258 0.03422 0.0155 1.0000 0.1109
-4.750 -0.5561 0.04102 0.03237 0.0195 1.0000 0.1078
-4.500 -0.5538 0.03968 0.03062 0.0232 1.0000 0.1051
-4.250 -0.0371 0.02625 0.01851 -0.0320 1.0000 1.0000
-4.000 -0.0189 0.02573 0.01775 -0.0317 1.0000 1.0000
-3.750 -0.0011 0.02532 0.01718 -0.0316 1.0000 1.0000
-3.500 0.0155 0.02507 0.01681 -0.0314 1.0000 1.0000
-3.250 0.0251 0.02522 0.01696 -0.0306 1.0000 1.0000
-3.000 0.0030 0.02674 0.01858 -0.0262 1.0000 1.0000
-2.750 0.0623 0.02652 0.01804 -0.0354 0.9698 1.0000
-2.500 0.1442 0.02554 0.01666 -0.0472 0.9379 1.0000
-2.250 0.2090 0.02481 0.01559 -0.0551 0.9059 1.0000
-2.000 0.2488 0.02461 0.01510 -0.0578 0.8751 1.0000
-1.750 0.2746 0.02472 0.01497 -0.0576 0.8482 1.0000
-1.500 0.2952 0.02499 0.01505 -0.0567 0.8243 1.0000
-1.250 0.3149 0.02526 0.01515 -0.0554 0.8043 1.0000
-1.000 0.3340 0.02560 0.01536 -0.0542 0.7851 1.0000
-0.750 0.3535 0.02597 0.01563 -0.0531 0.7681 1.0000
-0.500 0.3728 0.02637 0.01593 -0.0520 0.7522 1.0000
-0.250 0.3930 0.02678 0.01624 -0.0510 0.7375 1.0000
0.000 0.4129 0.02720 0.01657 -0.0499 0.7242 1.0000
0.250 0.4324 0.02768 0.01699 -0.0489 0.7110 1.0000
0.500 0.4519 0.02825 0.01754 -0.0481 0.6979 1.0000
0.750 0.4713 0.02888 0.01815 -0.0474 0.6859 1.0000
1.000 0.4906 0.02945 0.01868 -0.0463 0.6752 1.0000
1.250 0.5099 0.03003 0.01923 -0.0452 0.6645 1.0000
1.500 0.5285 0.03091 0.02016 -0.0447 0.6533 1.0000
1.750 0.5474 0.03161 0.02084 -0.0437 0.6439 1.0000
2.000 0.5658 0.03238 0.02163 -0.0427 0.6338 1.0000
2.250 0.5828 0.03349 0.02280 -0.0421 0.6238 1.0000
2.500 0.6023 0.03403 0.02333 -0.0406 0.6160 1.0000
2.750 0.6164 0.03550 0.02493 -0.0402 0.6053 1.0000
3.000 0.6333 0.03648 0.02593 -0.0390 0.5972 1.0000
3.250 0.6471 0.03784 0.02738 -0.0382 0.5880 1.0000
3.500 0.6593 0.03935 0.02896 -0.0371 0.5794 1.0000
3.750 0.6737 0.04052 0.03019 -0.0357 0.5712 1.0000
4.000 0.6792 0.04268 0.03248 -0.0346 0.5626 1.0000
4.250 0.6940 0.04374 0.03358 -0.0329 0.5549 1.0000
4.500 0.6887 0.04674 0.03670 -0.0314 0.5467 1.0000
4.750 0.7022 0.04791 0.03792 -0.0296 0.5394 1.0000
5.000 0.6855 0.05155 0.04163 -0.0274 0.5321 1.0000
5.250 0.6817 0.05396 0.04410 -0.0251 0.5253 1.0000
5.500 0.6762 0.05648 0.04665 -0.0226 0.5193 1.0000
5.750 0.6260 0.06123 0.05135 -0.0180 0.5158 1.0000
6.000 0.5812 0.06465 0.05469 -0.0124 0.5151 1.0000
6.250 0.5509 0.06762 0.05761 -0.0083 0.5148 1.0000
6.500 0.5284 0.07040 0.06036 -0.0050 0.5151 1.0000
6.750 0.5123 0.07322 0.06316 -0.0026 0.5175 1.0000
7.000 0.5093 0.07616 0.06613 -0.0015 0.5228 1.0000
9.500 0.4578 0.10230 0.09238 0.0079 0.5249 1.0000
9.750 0.4590 0.10443 0.09455 0.0087 0.5130 1.0000
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Polar data table (+)
Polar graphs
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