EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 500,000 Max Cl/Cd: 107.21 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e908-il-500000.txt Download as CSV file: xf-e908-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4199 0.08580 0.08367 -0.0531 0.9852 0.0079
-8.000 -0.4148 0.08100 0.07888 -0.0578 0.9837 0.0080
-7.750 -0.4208 0.07726 0.07518 -0.0595 0.9800 0.0081
-7.500 -0.4280 0.07278 0.07073 -0.0631 0.9751 0.0081
-7.250 -0.4156 0.06494 0.06281 -0.0744 0.9719 0.0081
-7.000 -0.4118 0.05931 0.05709 -0.0786 0.9680 0.0081
-6.750 -0.4081 0.05436 0.05201 -0.0805 0.9632 0.0082
-6.500 -0.3926 0.04861 0.04606 -0.0843 0.9607 0.0085
-6.250 -0.3714 0.04313 0.04031 -0.0877 0.9591 0.0090
-6.000 -0.3619 0.03930 0.03624 -0.0869 0.9551 0.0094
-5.750 -0.3468 0.03534 0.03198 -0.0865 0.9513 0.0102
-5.500 -0.3209 0.03215 0.02843 -0.0871 0.9495 0.0122
-4.000 -0.1591 0.01748 0.01162 -0.0881 0.9385 0.0155
-3.750 -0.1279 0.01640 0.01046 -0.0885 0.9371 0.0130
-3.500 -0.0965 0.01501 0.00893 -0.0892 0.9361 0.0122
-3.250 -0.0636 0.01403 0.00782 -0.0903 0.9351 0.0119
-3.000 -0.0290 0.01330 0.00688 -0.0917 0.9343 0.0128
-2.750 0.0049 0.01205 0.00609 -0.0933 0.9336 0.1641
-2.500 0.0234 0.01128 0.00602 -0.0922 0.9294 0.3552
-2.250 0.0470 0.01050 0.00601 -0.0920 0.9264 0.5817
-2.000 0.0766 0.01032 0.00607 -0.0924 0.9245 0.6853
-1.750 0.1096 0.01024 0.00598 -0.0935 0.9232 0.7092
-1.500 0.1440 0.01014 0.00581 -0.0950 0.9221 0.7247
-1.250 0.1785 0.01005 0.00570 -0.0965 0.9212 0.7399
-1.000 0.2139 0.00993 0.00559 -0.0982 0.9205 0.7518
-0.750 0.2289 0.01003 0.00570 -0.0955 0.9140 0.7615
-0.500 0.2610 0.00994 0.00561 -0.0966 0.9121 0.7716
-0.250 0.2948 0.00983 0.00551 -0.0979 0.9107 0.7832
0.000 0.3294 0.00967 0.00540 -0.0994 0.9097 0.7961
0.250 0.3641 0.00949 0.00529 -0.1009 0.9088 0.8119
0.500 0.3993 0.00929 0.00517 -0.1025 0.9082 0.8308
0.750 0.4359 0.00911 0.00507 -0.1044 0.9076 0.8450
1.000 0.4737 0.00894 0.00497 -0.1066 0.9071 0.8558
1.250 0.4829 0.00895 0.00511 -0.1025 0.8985 0.8702
1.500 0.5195 0.00875 0.00499 -0.1045 0.8973 0.8813
1.750 0.5566 0.00854 0.00489 -0.1065 0.8963 0.8935
2.000 0.5943 0.00829 0.00477 -0.1086 0.8951 0.9077
2.250 0.6390 0.00696 0.00350 -0.1107 0.8760 0.9192
2.500 0.6647 0.00620 0.00229 -0.1082 0.7373 0.9417
2.750 0.6485 0.00824 0.00279 -0.0991 0.4313 1.0000
3.000 0.6347 0.01117 0.00383 -0.0919 0.0182 1.0000
3.250 0.6579 0.01157 0.00433 -0.0909 0.0135 1.0000
3.500 0.6797 0.01206 0.00493 -0.0896 0.0125 1.0000
3.750 0.7012 0.01253 0.00541 -0.0885 0.0088 1.0000
4.000 0.7159 0.01371 0.00672 -0.0857 0.0072 1.0000
4.250 0.7322 0.01585 0.00899 -0.0832 0.0067 1.0000
4.500 0.7610 0.01734 0.01054 -0.0832 0.0069 1.0000
4.750 0.7882 0.01795 0.01120 -0.0828 0.0077 1.0000
6.000 0.9352 0.03347 0.02824 -0.0796 0.0137 1.0000
6.250 0.9555 0.03520 0.03022 -0.0774 0.0119 1.0000
6.500 0.9708 0.03771 0.03300 -0.0748 0.0107 1.0000
6.750 0.9831 0.04040 0.03594 -0.0719 0.0098 1.0000
7.000 0.9930 0.04312 0.03889 -0.0690 0.0091 1.0000
7.250 1.0005 0.04588 0.04185 -0.0660 0.0086 1.0000
7.500 1.0059 0.04865 0.04481 -0.0630 0.0082 1.0000
7.750 1.0085 0.05156 0.04789 -0.0600 0.0079 1.0000
8.000 1.0069 0.05485 0.05137 -0.0564 0.0076 1.0000
8.250 1.0010 0.05850 0.05521 -0.0526 0.0074 1.0000
8.500 0.9896 0.06257 0.05947 -0.0485 0.0072 1.0000
8.750 0.9737 0.06637 0.06345 -0.0438 0.0071 1.0000
9.000 0.9548 0.06987 0.06708 -0.0391 0.0070 1.0000
9.250 0.9371 0.07327 0.07062 -0.0354 0.0069 1.0000
9.500 0.9177 0.07713 0.07460 -0.0325 0.0069 1.0000
9.750 0.9013 0.08088 0.07848 -0.0309 0.0069 1.0000
10.000 0.8866 0.08484 0.08254 -0.0303 0.0069 1.0000
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Polar data table (+)
Polar graphs
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