EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 50,000 Max Cl/Cd: 27.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e851-il-50000.txt Download as CSV file: xf-e851-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4440 0.09871 0.09221 -0.0204 1.0000 0.2969
-7.750 -0.4437 0.09590 0.08948 -0.0188 1.0000 0.3107
-7.500 -0.4462 0.09355 0.08707 -0.0167 1.0000 0.3286
-7.250 -0.4566 0.09189 0.08555 -0.0144 1.0000 0.3441
-7.000 -0.4575 0.08974 0.08349 -0.0110 1.0000 0.3710
-5.750 -0.5365 0.05569 0.04882 -0.0464 1.0000 0.1184
-5.500 -0.5199 0.05016 0.04285 -0.0474 1.0000 0.1018
-5.250 -0.4994 0.04529 0.03726 -0.0484 1.0000 0.0905
-5.000 -0.4769 0.04094 0.03226 -0.0488 1.0000 0.0841
-4.750 -0.4506 0.03779 0.02820 -0.0485 1.0000 0.0802
-4.500 -0.4255 0.03462 0.02454 -0.0481 1.0000 0.0813
-4.250 -0.4014 0.03233 0.02189 -0.0477 1.0000 0.0937
-4.000 -0.3759 0.02946 0.01881 -0.0467 1.0000 0.1031
-3.750 -0.3499 0.02707 0.01629 -0.0450 1.0000 0.1167
-3.500 -0.3265 0.02499 0.01437 -0.0437 1.0000 0.1573
-3.250 -0.2980 0.02090 0.01199 -0.0441 1.0000 0.3376
-3.000 -0.3072 0.02136 0.01378 -0.0318 1.0000 0.6781
-2.750 -0.3113 0.02171 0.01417 -0.0221 1.0000 0.7474
-2.500 -0.3148 0.02169 0.01411 -0.0131 1.0000 0.8024
-2.250 -0.3190 0.02140 0.01380 -0.0043 1.0000 0.8565
-2.000 -0.2964 0.02127 0.01347 0.0007 1.0000 0.9371
-1.750 -0.1643 0.02169 0.01285 -0.0195 1.0000 0.9900
-1.500 -0.1490 0.02105 0.01191 -0.0204 1.0000 1.0000
-1.250 -0.1557 0.02021 0.01100 -0.0172 1.0000 1.0000
-1.000 -0.1442 0.01971 0.01030 -0.0171 1.0000 1.0000
-0.750 -0.1189 0.01956 0.00988 -0.0191 1.0000 1.0000
-0.500 -0.0901 0.01961 0.00964 -0.0214 1.0000 1.0000
-0.250 -0.0613 0.01976 0.00954 -0.0233 1.0000 1.0000
0.000 -0.0336 0.01999 0.00954 -0.0248 1.0000 1.0000
0.250 -0.0070 0.02026 0.00954 -0.0259 1.0000 1.0000
0.500 0.0185 0.02057 0.00968 -0.0266 1.0000 1.0000
0.750 0.0432 0.02091 0.00988 -0.0272 1.0000 1.0000
1.000 0.0672 0.02128 0.01014 -0.0276 1.0000 1.0000
1.250 0.0906 0.02168 0.01046 -0.0278 1.0000 1.0000
1.500 0.1135 0.02211 0.01084 -0.0280 1.0000 1.0000
1.750 0.1359 0.02257 0.01127 -0.0281 1.0000 1.0000
2.000 0.1580 0.02306 0.01175 -0.0282 1.0000 1.0000
2.250 0.1796 0.02359 0.01228 -0.0282 1.0000 1.0000
2.500 0.2008 0.02416 0.01288 -0.0282 1.0000 1.0000
2.750 0.2216 0.02477 0.01353 -0.0282 1.0000 1.0000
3.000 0.2419 0.02543 0.01426 -0.0282 1.0000 1.0000
3.250 0.2618 0.02614 0.01506 -0.0282 1.0000 1.0000
3.500 0.2812 0.02690 0.01604 -0.0281 1.0000 1.0000
3.750 0.3000 0.02773 0.01699 -0.0281 1.0000 1.0000
4.000 0.3182 0.02863 0.01803 -0.0282 1.0000 1.0000
4.250 0.3357 0.02961 0.01917 -0.0282 1.0000 1.0000
4.500 0.3525 0.03068 0.02043 -0.0284 1.0000 1.0000
4.750 0.3880 0.03239 0.02245 -0.0323 0.9887 1.0000
5.000 0.4684 0.03463 0.02546 -0.0436 0.9475 1.0000
5.250 0.6115 0.03342 0.02558 -0.0587 0.8602 1.0000
5.500 0.7450 0.02733 0.01649 -0.0507 0.1628 1.0000
5.750 0.8093 0.03188 0.02077 -0.0545 0.1088 1.0000
6.000 0.8507 0.03592 0.02516 -0.0552 0.0900 1.0000
6.250 0.8827 0.04023 0.02988 -0.0546 0.0853 1.0000
6.500 0.9027 0.04314 0.03327 -0.0526 0.0773 1.0000
6.750 0.9207 0.04710 0.03753 -0.0511 0.0726 1.0000
7.000 0.9384 0.05162 0.04244 -0.0492 0.0736 1.0000
7.250 0.9459 0.05508 0.04688 -0.0453 0.0789 1.0000
7.500 0.9537 0.05988 0.05213 -0.0428 0.0839 1.0000
7.750 0.9558 0.06458 0.05746 -0.0398 0.0928 1.0000
8.000 0.9553 0.06983 0.06318 -0.0375 0.1049 1.0000
8.250 0.9486 0.07574 0.06950 -0.0359 0.1220 1.0000
8.500 0.8783 0.07503 0.06941 -0.0289 0.1272 1.0000
8.750 0.8458 0.07909 0.07364 -0.0266 0.1286 1.0000
9.000 0.8149 0.08386 0.07850 -0.0261 0.1297 1.0000
9.250 0.7847 0.08968 0.08436 -0.0279 0.1313 1.0000
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Polar data table (+)
Polar graphs
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