EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 50,000 Max Cl/Cd: 22.19 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e908-il-50000.txt Download as CSV file: xf-e908-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5086 0.10109 0.09500 -0.0173 1.0000 0.2472
-7.000 -0.5021 0.09737 0.09131 -0.0154 1.0000 0.2557
-6.750 -0.5178 0.09537 0.08943 -0.0130 1.0000 0.2651
-6.500 -0.5440 0.09407 0.08828 -0.0130 1.0000 0.2753
-6.250 -0.5448 0.09085 0.08514 -0.0111 1.0000 0.2890
-6.000 -0.5277 0.08709 0.08138 -0.0063 1.0000 0.3095
-5.000 -0.5040 0.05771 0.05086 -0.0425 1.0000 0.1268
-4.750 -0.4782 0.05078 0.04326 -0.0456 1.0000 0.0996
-4.500 -0.4508 0.04549 0.03710 -0.0475 1.0000 0.0881
-4.250 -0.4266 0.04173 0.03291 -0.0480 1.0000 0.0869
-4.000 -0.3993 0.03833 0.02885 -0.0485 1.0000 0.0874
-3.750 -0.3714 0.03532 0.02526 -0.0485 1.0000 0.0877
-3.500 -0.3434 0.03261 0.02205 -0.0481 1.0000 0.0874
-3.250 -0.3157 0.03040 0.01936 -0.0472 1.0000 0.0887
-3.000 -0.2907 0.02837 0.01731 -0.0459 1.0000 0.0950
-2.750 -0.2662 0.02684 0.01567 -0.0442 1.0000 0.1075
-2.500 -0.2396 0.02514 0.01423 -0.0436 1.0000 0.1661
-2.250 -0.2359 0.02096 0.01405 -0.0308 1.0000 1.0000
-2.000 -0.2151 0.02075 0.01309 -0.0308 1.0000 1.0000
-1.750 -0.1919 0.02072 0.01244 -0.0311 1.0000 1.0000
-1.500 -0.1678 0.02078 0.01183 -0.0315 1.0000 1.0000
-1.250 -0.1436 0.02091 0.01150 -0.0318 1.0000 1.0000
-1.000 -0.1197 0.02109 0.01129 -0.0320 1.0000 1.0000
-0.750 -0.0959 0.02131 0.01117 -0.0322 1.0000 1.0000
-0.500 -0.0725 0.02158 0.01115 -0.0323 1.0000 1.0000
-0.250 -0.0494 0.02187 0.01117 -0.0324 1.0000 1.0000
0.000 -0.0264 0.02219 0.01114 -0.0324 1.0000 1.0000
0.250 -0.0038 0.02255 0.01130 -0.0323 1.0000 1.0000
0.500 0.0184 0.02293 0.01152 -0.0323 1.0000 1.0000
0.750 0.0404 0.02335 0.01180 -0.0322 1.0000 1.0000
1.000 0.0621 0.02380 0.01213 -0.0321 1.0000 1.0000
1.250 0.0835 0.02427 0.01252 -0.0319 1.0000 1.0000
1.500 0.1046 0.02478 0.01297 -0.0318 1.0000 1.0000
1.750 0.1254 0.02532 0.01346 -0.0316 1.0000 1.0000
2.000 0.1460 0.02589 0.01400 -0.0315 1.0000 1.0000
2.250 0.1662 0.02650 0.01460 -0.0313 1.0000 1.0000
2.500 0.1862 0.02714 0.01525 -0.0312 1.0000 1.0000
2.750 0.2059 0.02782 0.01596 -0.0310 1.0000 1.0000
3.000 0.2253 0.02853 0.01673 -0.0308 1.0000 1.0000
3.250 0.2445 0.02929 0.01757 -0.0307 1.0000 1.0000
3.500 0.2632 0.03009 0.01854 -0.0305 1.0000 1.0000
3.750 0.2817 0.03093 0.01949 -0.0304 1.0000 1.0000
4.000 0.2999 0.03183 0.02052 -0.0303 1.0000 1.0000
4.250 0.3178 0.03277 0.02161 -0.0302 1.0000 1.0000
4.500 0.3353 0.03377 0.02278 -0.0301 1.0000 1.0000
4.750 0.3524 0.03483 0.02403 -0.0301 1.0000 1.0000
5.000 0.3691 0.03596 0.02537 -0.0301 1.0000 1.0000
5.250 0.3854 0.03717 0.02697 -0.0301 1.0000 1.0000
5.500 0.4012 0.03846 0.02853 -0.0302 1.0000 1.0000
5.750 0.4684 0.04162 0.03241 -0.0400 0.9682 1.0000
6.000 0.8872 0.03999 0.02887 -0.0655 0.0730 1.0000
6.250 0.9263 0.04517 0.03427 -0.0666 0.0761 1.0000
6.500 0.9452 0.04718 0.03728 -0.0626 0.0839 1.0000
6.750 0.9666 0.05094 0.04167 -0.0600 0.0934 1.0000
7.000 0.9830 0.05501 0.04644 -0.0568 0.1078 1.0000
7.250 0.9993 0.05958 0.05172 -0.0539 0.1314 1.0000
7.500 1.0082 0.06459 0.05760 -0.0509 0.1708 1.0000
7.750 1.0060 0.07097 0.06487 -0.0500 0.2346 1.0000
8.000 0.9766 0.07540 0.06967 -0.0479 0.2550 1.0000
8.250 0.9457 0.08032 0.07478 -0.0472 0.2762 1.0000
8.500 0.9112 0.08472 0.07918 -0.0458 0.2787 1.0000
8.750 0.8755 0.09092 0.08534 -0.0482 0.2905 1.0000
9.000 0.8311 0.10119 0.09549 -0.0586 0.3403 1.0000
9.250 0.7578 0.09433 0.08904 -0.0370 0.2354 1.0000
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Polar data table (+)
Polar graphs
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